81 FR 39547 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 117 (June 17, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 117 (June 17, 2016)
| Page Range | 39547-39553 | |
| FR Document | 2016-13051 |
[Federal Register Volume 81, Number 117 (Friday, June 17, 2016)] [Rules and Regulations] [Pages 39547-39553] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-13051] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2011-0027; Directorate Identifier 2010-NM-127-AD; Amendment 39-18543; AD 2016-11-16] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of thrust reverser (T/R) events related to thermal damage of the T/R inner wall. Depending on the airplane configuration, this AD requires a records review and applicable repetitive inspections, replacements, and installations of the T/R inner wall; and related investigative and corrective actions if necessary. This AD also requires installation of serviceable T/R halves, which would terminate the repetitive actions. This AD also requires revising the inspection or maintenance program by incorporating new airworthiness limitations. We are issuing this AD to detect and correct a degraded T/R inner wall panel. A degraded T/R inner wall panel could lead to failure of the T/R and adjacent components and their consequent separation from the airplane, which could result in a rejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If a T/R inner wall overheats, separated components could cause structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground. DATES: This AD is effective July 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 22, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2011- 0027. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2011- 0027; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6501; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. The SNPRM published in the Federal Register on September 25, 2015 (80 FR 57744) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 20, 2011 (76 FR 3561) (``the NPRM''). The NPRM proposed to require repetitive inspections for degradation of T/R structure and sealant, and related investigative and corrective actions if [[Page 39548]] necessary. The NPRM was prompted by reports of T/R events related to thermal damage of the T/R inner wall. The SNPRM proposed to revise the NPRM by adding different repetitive inspection requirements for T/R halves with a thermal protective system installed. The SNPRM also proposed to revise the NPRM by requiring installation of serviceable T/ R halves, which would terminate the repetitive inspections. The SNPRM also proposed to revise the inspection or maintenance program by incorporating new airworthiness limitations. We are issuing this AD to detect and correct a degraded T/R inner wall panel. A degraded T/R inner wall panel could lead to failure of the T/R and adjacent components and their consequent separation from the airplane, which could result in an RTO and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If a T/R inner wall overheats, separated components could cause structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA's response to each comment. Request To Change Compliance Reference Boeing requested that we revise paragraph (k)(2) of the proposed AD (in the SNPRM) by adding ``table 5'' to the reference to the Compliance paragraph in Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015. Boeing stated that this change would be consistent with how paragraph (k)(1) of the proposed AD (in the SNPRM) refers to the Compliance paragraph. We agree with the commenter's request for the reason provided. We have revised paragraph (k)(2) of this AD accordingly. Request To Modify Alternative Method of Compliance (AMOC) Statement Boeing requested that the AMOC statement specified in paragraph (r)(3) of the proposed AD (in the SNPRM) be revised by adding a sentence to allow an AMOC for the serviceable T/R assembly to be transferred to other airplanes. Boeing stated that an AMOC provided for a repaired and serviceable unit is able to be attached to and travel with the repaired unit. Boeing added that a serviceable unit is a rotable part and can be installed on multiple airplanes during the life of the unit. Boeing noted that paragraph (l)(3) of AD 2015-19-16, Amendment 39-18278 (80 FR 59570, October 2, 2015) contains language similar to the requested language. We disagree with the request because we are now able to issue an AMOC that applies to multiple products operated by a single operator (commonly referred to as a fleet AMOC). This procedure allows AMOCs to address rotable parts. We have not changed this AD in this regard. Request To Update Service Information Boeing requested that the revision date of Boeing 777 Maintenance Planning Data (MPD) Document Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001-9, Revision dated October 2014, be updated to reflect the latest FAA- approved revision. Boeing stated that AWL 78-AWL-01, Thrust Reverser Thermal Protection System, was revised recently to include Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014, in the applicability note of the AWL. We agree to reference the most recent revision of Boeing 777 MPD Document Section 9, AWLs and CMRs, D622W001-9 (which is referred to as Temporary Revision (TR) 09-030, Revision dated November 2015, on MyBoeingFleet.com), because the new applicability note clarifies that AWL 78-AWL-01 applies to T/R halves on which the actions specified in Boeing Alert Service Bulletin 777-78A0094 have been done. As a result, we have revised the introductory text to paragraph (n) of this AD accordingly. We have also added a new paragraph (p)(5) to this AD to provide credit for accomplishing the revision required by paragraph (n) of this AD using Boeing 777 MPD Document, Section 9, AWLs and CMRs, D622W001-9, Revision dated October 2014. Request To Modify Initial Inspection Boeing requested that paragraph (n)(1) of the proposed AD (in the SNPRM) be revised to allow deferral of the initial inspection for AWL 78-AWL-01, Thrust Reverser Thermal Protection System. Boeing stated that the compliance time should be 1,125 days or 6,000 flight cycles, whichever occurs first, after the last inspection for AWL 78-AWL-01, Thrust Reverser Thermal Protection System, ``for T/Rs that have already incorporated 78-AWL-01.'' Boeing stated that when the AD becomes effective, T/R halves on which Boeing Alert Service Bulletin 777- 78A0094 and AWL 78-AWL-01, Thrust Reverser Thermal Protection System, have been incorporated are not subject to the inspections specified in paragraph (i) of the proposed AD (in the SNPRM) and should not be required to do the inspection required by AWL 78-AWL-01 concurrent with the next inspection required by paragraph (i) of this AD or within 30 days after the effective date of this AD, whichever occurs later. We agree with allowing deferral of the initial inspection for AWL 78-AWL-01, Thrust Reverser Thermal Protection System, for the reasons provided by the commenter. We have revised the compliance time for AWL 78-AWL-01, Thrust Reverser Thermal Protection System, as requested by the commenter. We have revised the introductory text to paragraph (n), and reformatted and revised paragraphs (n)(1) and (n)(2) of this AD, to accommodate the commenter's request. We clarified the affected airplanes for the compliance as specified in paragraph (n)(1) of this AD by stating, ``For airplanes on which any inspections required by paragraph (i) of this AD are done.'' We clarified the affected airplanes for the compliance as specified in paragraph (n)(2) of this AD by stating, ``For airplanes on which the installation required by paragraph (l) of this AD is done.'' Request To Review Inspection Methods American Airlines requested that the FAA review the inspection methods and instructions required in paragraph (i) of the proposed AD (in the SNPRM) when doing a nondestructive test (NDT) inspection for delaminations and disbonds; and ensuring false positive findings are prevented or minimized. American Airlines stated that they inspected eight T/R inner walls in accordance with paragraph (i)(1) of the proposed AD (in the SNPRM) and found disbonded material. American Airlines stated that after they contacted the original equipment manufacturer (OEM) and re-inspected, several units were determined to be false positives. American Airlines surmised that the instructions or possible training for inspections may not be sufficient. We acknowledge the commenter's concern. However, we have determined the NDT inspections for disbonds and damage required in paragraph (i) and associated service information produce reliable inspection results and adequately detect disbonds and damage. Through technical discussion with the OEM, we understand that the false positive indications were a result of a maintenance vendor using a non-OEM inspection manual that had a faulty NDT inspection standard. We have not revised this AD in this regard. [[Page 39549]] Request To Review Airworthiness Limitation Inspection Procedures American Airlines stated it had a T/R inner wall that required repair, but the damage would not have been detected by the inspection specified in Airworthiness Limitation 78-AWL-02, Thrust Reverser Inner Wall, as specified in Boeing MPD Document, Section 9, AWLs and CMRs, D622W001-9, Revision dated October 2014. American Airlines stated the damage would likely have passed inspection because it did not indicate any heat discoloration, and other areas of disbonds or damage on the inner wall could be potentially missed after the incorporation of Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014, and AWL 78-AWL-02. We infer the commenter is requesting that we review AWL 78- AWL-02 to ensure that thermal damage on the inner wall is not missed. We acknowledge the commenter's concern, and we might consider additional rulemaking to address that concern in the future. We contacted Boeing, and Boeing stated they are working with American Airlines to determine if a change needs to be made to the service information. However, until such additional action is identified, we consider it appropriate to proceed with issuance of this final rule to address the identified unsafe condition. We have not changed this final rule in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010. This service information describes procedures for a review of the airplane maintenance records to determine whether sealant was added to insulation blankets around compression pad fittings and the powered door opening system (PDOS) fitting; inspections of the T/R structure; and related investigative and corrective actions. Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014. This service information describes procedures for installing serviceable T/R halves. Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015; and Boeing Special Attention Service Bulletin 777-78- 0071, Revision 2, dated July 23, 2013. This service information describes, among other actions, procedures for inspections of the T/R structure, and related investigative and corrective actions, if necessary. Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013, also describes, for airplanes on which the actions specified in Boeing Special Attention Service Bulletin 777- 78-0071, dated November 29, 2009, have been done, procedures for installation of click bond covers and a bracket, a general visual inspection of the compression fitting for incorrect pin orientation, and related investigative and corrective actions, if necessary. Boeing 777 Maintenance Planning Data (MPD) Document, Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001 9, Revision dated November 2015. This service information provides required AWLs and CMRs for The Boeing Company Model 777 airplanes. The two AWLs specifically required by this AD are AWL 78-AWL-01, Thrust Reverser Thermal Protection System, which describes an inspection of the T/R thermal protection system on both engines; and AWL 78 AWL-02, which describes an inspection of the T/R inner wall. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 55 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Average labor Cost per Action Work hours rate per hour Parts cost product Fleet cost ---------------------------------------------------------------------------------------------------------------- Actions per Boeing Alert Up to 79 work- $85 $0............. Up to $6,715 $0 (No Service Bulletin hours, per T/R per T/R half. airplanes on 777[dash]78A0065, Revision half. the U.S. 2, dated May 6, 2010. Register are in the configuration specified in Boeing Alert Service Bulletin 777[dash]78A00 65, Revision 2, dated May 6, 2010.) Actions per Boeing Special Up to 48 work- 85 $0............. Up to $4,080 Up to $897,600 Attention Service Bulletin hours, per T/R per T/R half. (4 T/R halves 777[dash]78[dash]0071, half. per airplane). Revision 2, dated July 23, 2013. Inspections per Boeing Up to 39 work- 85 $0............. Up to $3,315 $0 (No Service Bulletin hours, per T/R per T/R half. airplanes on 777[dash]78[dash]0082, half. the U.S. Revision 1, dated June 15, Register are 2015. in the configuration specified in Boeing Service Bulletin 777[dash]78[da sh]0082, Revision 1, dated June 15, 2015.) Maintenance or Inspection 1 work-hour.... 85 $0............. $85............ $4,675. Program Revision. [[Page 39550]] T/R half installation per Up to 206 work- 85 Up to $400,651 Up to $418,161 Up to Boeing Alert Service hours, per T/R per T/R half per T/R half. $91,995,420 (4 Bulletin 777[dash]78A0094, half. \1\. T/R halves per dated July 29, 2014. airplane).\2\ ---------------------------------------------------------------------------------------------------------------- \1\ The cost of parts is split into two major parts: (1) Thermal protection system (TPS) blankets and (2) inner wall structure. The vast majority of the work associated with the TPS upgrade has already been completed. In addition, nearly half of the inner wall structure modification has already been done. \2\ The fleet cost estimate above is based on a general estimate for a given airplane with two engines having two T/R halves for each engine. Not all tasks required by this AD and specified in the service information would need to be done for a given T/R half. For a given TR half, it may only be necessary to accomplish certain actions or none for compliance, depending on its configuration status. We have no data to determine any given T/R half configuration to determine the cost for each T/R half to do the applicable actions for that T/R half. The majority of this cost has already been incurred. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-11-16 The Boeing Company: Amendment 39-18543; Docket No. FAA- 2011-0027; Directorate Identifier 2010-NM-127-AD. (a) Effective Date This AD is effective July 22, 2016. (b) Affected ADs This AD affects AD 2005-07-24, Amendment 39-14049 (70 FR 18285, April 11, 2005). (c) Applicability This AD applies to The Boeing Company Model 777-200 and -300 series airplanes, certificated in any category, equipped with Rolls- Royce Model RB211-Trent 800 engines. (d) Subject Air Transport Association (ATA) of America Code 78, Engine exhaust. (e) Unsafe Condition This AD was prompted by reports of thrust reverser (T/R) events related to thermal damage of the T/R inner wall. We are issuing this AD to detect and correct a degraded T/R inner wall panel. A degraded T/R inner wall panel could lead to failure of the T/R and adjacent components and their consequent separation from the airplane, which could result in a rejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If a T/R inner wall overheats, separated components could cause structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Records Review, Inspections, and Related Investigative and Corrective Actions for Airplanes With Pre-Thermal Protection System (TPS) Insulation Blankets (Part Numbers (P/Ns) 315W5113-(XX) and 315W5010-(XX)) Installed For airplanes with pre-TPS insulation blankets, P/Ns 315W5113- (XX) and 315W5010-(XX): Except as required by paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, at the applicable time in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, review the airplane maintenance records to determine whether sealant was added to insulation blankets around the compression pad fittings and the powered door opening system (PDOS) fitting; do the applicable actions specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of this AD; and do all applicable related investigative and corrective actions; in accordance with the applicable work packages of the Accomplishment Instructions of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, except as required by paragraph (h)(5) of this AD. Do all applicable related investigative and corrective actions before further flight. [[Page 39551]] Repeat the applicable inspections, replacement, and installations required by paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010. (1) Do a detailed inspection of all T/R inner wall insulation blanket edges, grommet holes, penetrations, and seams for sealant that is cracked, has gaps, is loose, or is missing; do a general visual inspection of click bond studs, blanket studs, and temporary fasteners; and replace sealant as applicable. (2) Do the actions specified by either paragraph (g)(2)(i) or (g)(2)(ii) of this AD. (i) Do a full inner wall panel nondestructive test (NDT) inspection for delamination and disbonding of each T/R half, and do a general visual inspection for areas of thermal degradation. (ii) Do a limited area NDT inspection of the inner wall panel of each T/R half for delamination and disbonding, and do a general visual inspection for areas of thermal degradation. (3) Do a general visual inspection of the T/R perforated wall aft of the intermediate pressure compressor 8th stage (IP8) and the high pressure compressor 3rd stage (HP3) bleed port exits for a color that is different from that of the general area. (4) Do a detailed inspection of the PDOS lug bushings on the upper number 1 compression pad fittings to detect hole elongation, deformation, and contact with the PDOS actuator; and install a PDOS actuator rod and sealant. (5) Do an NDT inspection for unsatisfactory number 1 upper and numbers 1 and 2 lower compression pad fittings. (6) Install and seal insulation blankets. (h) Exceptions to Specifications of Boeing Alert Service Bulletin 777- 78A0065, Revision 2, Dated May 6, 2010 (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, specifies a compliance time ``after the date on the original issue of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where table 2 of paragraph 1.E., ``Compliance,'' in Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, specifies a compliance time of ``2,000 flight cycles after the date of the operator's own inspections,'' for doing Work Packages 2 and 5, or Work Packages 5 and 6, this AD requires compliance within 2,000 flight cycles after the date of the operator's own inspections, or within 12 months after the effective date of this AD, whichever occurs later. (3) Where the Condition column in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, refers to a T/R half that has or has not been inspected before ``the date on this service bulletin,'' this AD requires compliance for each corresponding T/R half that has or has not been inspected before the effective date of this AD. (4) Where the Condition column in tables 2 and 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, refers to ``total flight cycles,'' this AD applies to each T/R half with the specified total flight cycles as of the effective date of this AD. (5) Where Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (i) Repetitive NDT and Additional Inspections for Airplanes With TPS Insulation Blankets (P/N 315W5115-(XX)) Installed For airplanes with TPS insulation blankets, P/N 315W5115-(XX): Within 2,000 flight cycles after doing any NDT inspection specified in Boeing Special Attention Service Bulletin 777-78-0071; or within 2,000 flight cycles after doing any NDT inspection specified in Boeing Service Bulletin 777-78-0082; or within 30 days after the effective date of this AD; whichever occurs latest; do the inspections specified in paragraphs (i)(1) and (i)(2) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013, or in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015, as applicable; except as required by paragraph (m) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (i)(1) and (i)(2) of this AD thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013; or Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015; as applicable. (1) Do an NDT inspection of the full T/R inner wall panel for delaminations and disbonds. (2) Do a detailed inspection of the perforated side of the T/R inner wall aft of the IP8 and the HP3 bleed port exits for color that is different from the normal T/R perforated wall color. (j) Concurrent Requirements for Paragraph (i) of This AD For airplanes with TPS insulation blankets, P/N 315W5115-(XX), on which any action specified in Boeing Special Attention Service Bulletin 777-78-0071 have been done but the actions specified in paragraphs (j)(1) and (j)(2) of this AD have not been done: Prior to or concurrently with doing the inspection required by paragraph (i) of this AD, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013, except as required by paragraph (m) of this AD. (1) Install click bond covers and bracket and replace the washers. (2) Do a detailed inspection of the compression fitting for incorrect pin orientation, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (k) Repetitive Electronic Engine Control (EEC) Wire Bundle Inspections for Airplanes With TPS Insulation Blankets (P/N 315W5115-(XX)) Installed For airplanes with TPS insulation blankets, P/N 315W5115-(XX): Do the inspections specified in paragraphs (k)(1) or (k)(2) of this AD, as applicable. (1) For airplanes on which any inspection specified in Boeing Special Attention Service Bulletin 777-78-0071 has been done: Within 2,000 flight hours after doing a detailed inspection of the EEC wire bundles and clips as specified in Boeing Special Attention Service Bulletin 777-78-0071, or within 500 flight hours after the effective date of this AD, whichever occurs later; do a detailed inspection of the EEC wire bundles and clips for damage, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-78- 0071, Revision 2, dated July 23, 2013, except as required by paragraph (m) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-78- 0071, Revision 2, dated July 23, 2013. (2) For airplanes on which any inspection specified in Boeing Service Bulletin 777-78-0082, has been done: Within 2,000 flight hours after doing a detailed inspection of the EEC wire bundles and clips as specified in Boeing Special Attention Service Bulletin 777- 78-0082, or within 500 flight hours after the effective date of this AD, whichever occurs later; do a detailed inspection for damage of the EEC wire bundles and clips, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015, except as required by paragraph (m) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 777-78- 0082, Revision 1, dated June 15, 2015. (l) T/R Inner Wall Installation Within 48 months after the effective date of this AD: Install serviceable T/R halves, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014, except as required by paragraph (m) of this AD. The definition of a serviceable T/R half is specified in Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014. Accomplishing the installation specified in this paragraph and the revision to the maintenance or inspection program required by paragraph (n) of this AD terminates the [[Page 39552]] actions required by paragraphs (g), (i), (j), and (k) of this AD. (m) Exceptions to Service Information Specified in Paragraphs (i), (j), (k), and (l) of This AD Where Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014; Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015; and Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013; specify to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (n) Revise the Maintenance or Inspection Program Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate Airworthiness Limitations 78-AWL-01, Thrust Reverser Thermal Protection System; and 78-AWL-02, Thrust Reverser Inner Wall; as specified in Boeing 777 Maintenance Planning Data (MPD) Document, Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001-9, Revision dated November 2015. The initial compliance times for AWLs 78-AWL-01, Thrust Reverser Thermal Protection System, and 78-AWL-02, Thrust Reverser Inner Wall, as specified in Boeing 777 MPD Document, Section 9, AWLs and CMRs, D622W001-9, Revision dated November 2015, are at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. (1) For airplanes on which any inspections required by paragraph (i) of this AD are done: Concurrent with the next inspection required by paragraph (i) of this AD, or within 30 days after the effective date of this AD, whichever occurs later. (2) For airplanes on which the installation required by paragraph (l) of this AD is done: At the later of the times specified in paragraph (n)(2)(i) and (n)(2)(ii) of this AD. (i) Within 1,125 days or 6,000 flight cycles, whichever occurs first after accomplishing the installation required by paragraph (l) of this AD. (ii) Within 30 days after the effective date of this AD. (o) No Alternative Actions or Intervals After the maintenance or inspection program, as applicable, has been revised as required by paragraph (n) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (r) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777- 78A0065, dated June 23, 2008; or Boeing Alert Service Bulletin 777- 78A0065, Revision 1, dated January 29, 2009. This service information is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions specified in paragraph (i) of this AD, if those actions were performed before the effective date of this AD using any service information specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD. This service information is not incorporated by reference in this AD. (i) Boeing Service Bulletin 777-78-0082, dated November 9, 2011. (ii) Boeing Special Attention Service Bulletin 777-78-0071, dated November 25, 2009. (iii) Boeing Special Attention Service Bulletin 777-78-0071, Revision 1, dated September 8, 2010. (3) This paragraph provides credit for the actions specified in paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777-78-0071, Revision 1, dated September 8, 2010. This service information is not incorporated by reference in this AD. (4) This paragraph provides credit for the actions specified in paragraph (k)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 777-78- 0082, dated November 9, 2011. This service information is not incorporated by reference in this AD. (5) This paragraph provides credit for the actions specified in paragraph (n) of this AD, if those actions were performed before the effective date of this AD using Boeing 777 MPD Document, Section 9, AWLs and CMRs, D622W001-9, Revision dated October 2014. This service information is not incorporated by reference in this AD. (q) Terminating Action for AD 2005-07-24, Amendment 39-14049 (70 FR 18285, April 11, 2005) Accomplishing the actions specified in paragraph (q)(1), (q)(2), or (q)(3) of this AD terminates the actions required by paragraphs (f), (g), and (h) of AD 2005-07-24, Amendment 39-14049 (70 FR 18285, April 11, 2005). (1) The actions required by paragraph (g) of this AD. (2) The inspections required by paragraphs (i) and (k) of this AD, and, as applicable, the actions required by paragraph (j) of this AD. (3) The installation specified in paragraph (l) of this AD. (r) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (s)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (s) Related Information (1) For more information about this AD, contact Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917- 6501; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (t)(3) and (t)(4) of this AD. (t) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010. (ii) Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014. (iii) Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15, 2015. (iv) Boeing Special Attention Service Bulletin 777-78-0071, Revision 2, dated July 23, 2013. (v) Boeing 777 Maintenance Planning Data (MPD) Document, Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001-9, Revision dated November 2015. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544- 5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. [[Page 39553]] Issued in Renton, Washington, on May 20, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-13051 Filed 6-16-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39547
(2) Repeat the borescope inspection Issued in Burlington, Massachusetts, on ADDRESSES: For service information
required by this AD every 300 hours since June 10, 2016. identified in this final rule, contact
last inspection. Colleen M. D’Alessandro, Boeing Commercial Airplanes,
(3) If any crack, loss of contact between the Manager, Engine & Propeller Directorate, Attention: Data & Services Management,
ferrule and diffuser axial vane, or any contact Aircraft Certification Service. P.O. Box 3707, MC 2H–65, Seattle, WA
between the injection manifold supply pipe [FR Doc. 2016–14234 Filed 6–16–16; 8:45 am] 98124–2207; telephone: 206–544–5000,
and the diffuser ferrule is found, remove the BILLING CODE 4910–13–P extension 1; fax: 206–766–5680;
diffuser case and replace the ferrule with a Internet: https://
part eligible for installation. www.myboeingfleet.com. You may view
(f) Credit for Previous Actions DEPARTMENT OF TRANSPORTATION this referenced service information at
the FAA, Transport Airplane
You may take credit for the actions Federal Aviation Administration Directorate, 1601 Lind Avenue SW.,
required by paragraph (e) of this AD if you
Renton, WA. For information on the
performed those actions using Turbomeca 14 CFR Part 39
S.A. MSB No. 298 72 2832, Version B, dated
availability of this material at the FAA,
October 12, 2015 or earlier versions, before [Docket No. FAA–2011–0027; Directorate call 425–227–1221. It is also available
the effective date of this AD. Identifier 2010–NM–127–AD; Amendment on the Internet at http://
39–18543; AD 2016–11–16] www.regulations.gov by searching for
(g) Alternative Methods of Compliance and locating Docket No. FAA–2011–
(AMOCs) RIN 2120–AA64 0027.
The Manager, Engine Certification Office, Airworthiness Directives; The Boeing Examining the AD Docket
FAA, may approve AMOCs for this AD. Use Company Airplanes
the procedures found in 14 CFR 39.19 to You may examine the AD docket on
make your request. You may email your AGENCY: Federal Aviation the Internet at http://
request to: ANE-AD-AMOC@faa.gov. Administration (FAA), DOT. www.regulations.gov by searching for
ACTION: Final rule. and locating Docket No. FAA–2011–
(h) Related Information 0027; or in person at the Docket
(1) For more information about this AD, SUMMARY: We are adopting a new Management Facility between 9 a.m.
contact Brian Kierstead, Aerospace Engineer, airworthiness directive (AD) for certain and 5 p.m., Monday through Friday,
Engine Certification Office, FAA, Engine & The Boeing Company Model 777–200 except Federal holidays. The AD docket
Propeller Directorate, 1200 District Avenue, and -300 series airplanes equipped with contains this AD, the regulatory
Burlington, MA 01803; phone: 781–238– Rolls-Royce Model RB211-Trent 800 evaluation, any comments received, and
7772; fax: 781–238–7199; email: engines. This AD was prompted by other information. The address for the
brian.kierstead@faa.gov. reports of thrust reverser (T/R) events Docket Office (phone: 800–647–5527) is
(2) Refer to MCAI European Aviation related to thermal damage of the T/R Docket Management Facility, U.S.
Safety Agency AD 2015–0209R1, dated April inner wall. Depending on the airplane Department of Transportation, Docket
20, 2016, for more information. You may configuration, this AD requires a records Operations, M–30, West Building
examine the MCAI in the AD docket on the Ground Floor, Room W12–140, 1200
review and applicable repetitive
Internet at http://www.regulations.gov by New Jersey Avenue SE., Washington,
inspections, replacements, and
searching for and locating it in Docket No. DC 20590.
installations of the T/R inner wall; and
FAA–2015–8257.
related investigative and corrective FOR FURTHER INFORMATION CONTACT:
(i) Material Incorporated by Reference actions if necessary. This AD also Kevin Nguyen, Aerospace Engineer,
(1) The Director of the Federal Register requires installation of serviceable T/R Propulsion Branch, ANM–140S, FAA,
approved the incorporation by reference halves, which would terminate the Seattle Aircraft Certification Office
(IBR) of the service information listed in this repetitive actions. This AD also requires (ACO), 1601 Lind Avenue SW., Renton,
paragraph under 5 U.S.C. 552(a) and 1 CFR revising the inspection or maintenance WA 98057–3356; phone: 425–917–6501;
part 51. program by incorporating new fax: 425–917–6590; email:
(2) You must use this service information airworthiness limitations. We are kevin.nguyen@faa.gov.
as applicable to do the actions required by issuing this AD to detect and correct a SUPPLEMENTARY INFORMATION:
this AD, unless the AD specifies otherwise. degraded T/R inner wall panel. A
(i) Turbomeca S.A. Alert MSB No. A298 72 degraded T/R inner wall panel could Discussion
2832, Version C, dated April 15, 2016. lead to failure of the T/R and adjacent We issued a supplemental notice of
(ii) Reserved. components and their consequent proposed rulemaking (SNPRM) to
(3) For Turbomeca S.A. service information separation from the airplane, which amend 14 CFR part 39 by adding an AD
identified in this AD, contact Turbomeca could result in a rejected takeoff (RTO) that would apply to certain The Boeing
S.A., 40220 Tarnos, France; phone: (33) 05 59 and cause asymmetric thrust and Company Model 777–200 and -300
74 40 00; fax: (33) 05 59 74 45 15. consequent loss of control of the series airplanes equipped with Rolls-
(4) You may view this service information airplane during reverse thrust operation. Royce Model RB211-Trent 800 engines.
at FAA, Engine & Propeller Directorate, 1200 If a T/R inner wall overheats, separated The SNPRM published in the Federal
District Avenue, Burlington, MA. For components could cause structural Register on September 25, 2015 (80 FR
information on the availability of this damage to the airplane, damage to other 57744) (‘‘the SNPRM’’). We preceded
material at the FAA, call 781–238–7125. airplanes, or possible injury to people the SNPRM with a notice of proposed
(5) You may view this service information on the ground. rulemaking (NPRM) that published in
ehiers on DSK5VPTVN1PROD with RULES
at the National Archives and Records DATES: This AD is effective July 22, the Federal Register on January 20,
Administration (NARA). For information on 2016. 2011 (76 FR 3561) (‘‘the NPRM’’). The
the availability of this material at NARA, call The Director of the Federal Register NPRM proposed to require repetitive
202–741–6030, or go to: http:// approved the incorporation by reference inspections for degradation of T/R
www.archives.gov/federal-register/cfr/ibr-
of certain publications listed in this AD structure and sealant, and related
locations.html.
as of July 22, 2016. investigative and corrective actions if
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![39550 Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations
ESTIMATED COSTS—Continued
Average
Action Work hours labor rate Parts cost Cost per product Fleet cost
per hour
T/R half installation per Boeing Up to 206 work- 85 Up to $400,651 Up to $418,161 Up to $91,995,420 (4 T/R halves
Alert Service Bulletin hours, per T/R per T/R half 1. per T/R half. per airplane).2
777-78A0094, dated July 29, half.
2014.
1 The cost of parts is split into two major parts: (1) Thermal protection system (TPS) blankets and (2) inner wall structure. The vast majority of
the work associated with the TPS upgrade has already been completed. In addition, nearly half of the inner wall structure modification has al-
ready been done.
2 The fleet cost estimate above is based on a general estimate for a given airplane with two engines having two T/R halves for each engine.
Not all tasks required by this AD and specified in the service information would need to be done for a given T/R half. For a given TR half, it may
only be necessary to accomplish certain actions or none for compliance, depending on its configuration status. We have no data to determine
any given T/R half configuration to determine the cost for each T/R half to do the applicable actions for that T/R half. The majority of this cost
has already been incurred.
We have received no definitive data (1) Is not a ‘‘significant regulatory (d) Subject
that would enable us to provide cost action’’ under Executive Order 12866, Air Transport Association (ATA) of
estimates for the on-condition actions (2) Is not a ‘‘significant rule’’ under America Code 78, Engine exhaust.
specified in this AD. DOT Regulatory Policies and Procedures
(e) Unsafe Condition
According to the manufacturer, some (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation This AD was prompted by reports of thrust
of the costs of this AD may be covered reverser (T/R) events related to thermal
under warranty, thereby reducing the in Alaska, and
(4) Will not have a significant damage of the T/R inner wall. We are issuing
cost impact on affected individuals. We this AD to detect and correct a degraded
do not control warranty coverage for economic impact, positive or negative, T/R inner wall panel. A degraded T/R inner
affected individuals. As a result, we on a substantial number of small entities wall panel could lead to failure of the T/R
have included all costs in our cost under the criteria of the Regulatory and adjacent components and their
estimate. Flexibility Act. consequent separation from the airplane,
which could result in a rejected takeoff (RTO)
Authority for This Rulemaking List of Subjects in 14 CFR Part 39 and cause asymmetric thrust and consequent
Air transportation, Aircraft, Aviation loss of control of the airplane during reverse
Title 49 of the United States Code safety, Incorporation by reference, thrust operation. If a T/R inner wall
specifies the FAA’s authority to issue Safety. overheats, separated components could cause
rules on aviation safety. Subtitle I, structural damage to the airplane, damage to
section 106, describes the authority of Adoption of the Amendment other airplanes, or possible injury to people
the FAA Administrator. Subtitle VII: Accordingly, under the authority on the ground.
Aviation Programs, describes in more delegated to me by the Administrator, (f) Compliance
detail the scope of the Agency’s the FAA amends 14 CFR part 39 as Comply with this AD within the
authority. follows: compliance times specified, unless already
We are issuing this rulemaking under done.
the authority described in Subtitle VII, PART 39—AIRWORTHINESS
Part A, Subpart III, Section 44701: DIRECTIVES (g) Records Review, Inspections, and Related
Investigative and Corrective Actions for
‘‘General requirements.’’ Under that Airplanes With Pre-Thermal Protection
section, Congress charges the FAA with ■ 1. The authority citation for part 39
continues to read as follows: System (TPS) Insulation Blankets (Part
promoting safe flight of civil aircraft in Numbers (P/Ns) 315W5113–(XX) and
air commerce by prescribing regulations Authority: 49 U.S.C. 106(g), 40113, 44701. 315W5010–(XX)) Installed
for practices, methods, and procedures For airplanes with pre-TPS insulation
§ 39.13 [Amended]
the Administrator finds necessary for blankets, P/Ns 315W5113–(XX) and
safety in air commerce. This regulation ■ 2. The FAA amends § 39.13 by adding 315W5010–(XX): Except as required by
is within the scope of that authority the following new airworthiness paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of
because it addresses an unsafe condition directive (AD): this AD, at the applicable time in paragraph
that is likely to exist or develop on 2016–11–16 The Boeing Company: 1.E., ‘‘Compliance,’’ of Boeing Alert Service
products identified in this rulemaking Amendment 39–18543; Docket No. Bulletin 777–78A0065, Revision 2, dated
action. FAA–2011–0027; Directorate Identifier May 6, 2010, review the airplane
2010–NM–127–AD. maintenance records to determine whether
Regulatory Findings sealant was added to insulation blankets
(a) Effective Date around the compression pad fittings and the
This AD will not have federalism This AD is effective July 22, 2016. powered door opening system (PDOS) fitting;
implications under Executive Order do the applicable actions specified in
13132. This AD will not have a (b) Affected ADs paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
substantial direct effect on the States, on This AD affects AD 2005–07–24, and (g)(6) of this AD; and do all applicable
the relationship between the national Amendment 39–14049 (70 FR 18285, April related investigative and corrective actions;
ehiers on DSK5VPTVN1PROD with RULES
government and the States, or on the 11, 2005). in accordance with the applicable work
distribution of power and packages of the Accomplishment Instructions
(c) Applicability of Boeing Alert Service Bulletin 777–
responsibilities among the various This AD applies to The Boeing Company 78A0065, Revision 2, dated May 6, 2010,
levels of government. Model 777–200 and –300 series airplanes, except as required by paragraph (h)(5) of this
For the reasons discussed above, I certificated in any category, equipped with AD. Do all applicable related investigative
certify that this AD: Rolls-Royce Model RB211-Trent 800 engines. and corrective actions before further flight.
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![Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39553
Issued in Renton, Washington, on May 20, Services Dept., P.O. Box 1357, 2130 EL prevent the potential of ignition sources
2016. Hoofddorp, the Netherlands; telephone inside fuel tanks, which, in combination
Victor Wicklund, +31 (0)88–6280–350; fax +31 (0)88– with flammable fuel vapors, could result
Acting Manager, Transport Airplane 6280–111; email technicalservices@ in fuel tank explosions and consequent
Directorate, Aircraft Certification Service. fokker.com; Internet http:// loss of the airplane.
[FR Doc. 2016–13051 Filed 6–16–16; 8:45 am] www.myfokkerfleet.com. You may view The European Aviation Safety Agency
BILLING CODE 4910–13–P this referenced service information at (EASA), which is the Technical Agent
the FAA, Transport Airplane for the Member States of the European
Directorate, 1601 Lind Avenue SW., Union, has issued EASA Airworthiness
DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the Directive 2015–0029, dated February 24,
availability of this material at the FAA, 2015 (referred to after this as the
Federal Aviation Administration call 425–227–1221. It is also available Mandatory Continuing Airworthiness
on the Internet at http:// Information, or ‘‘the MCAI’’), to correct
14 CFR Part 39 www.regulations.gov by searching for an unsafe condition on all Model F.27
[Docket No. FAA–2015–8137; Directorate and locating Docket Number FAA– Mark 050, 200, 300, 400, 500, 600, and
Identifier 2014–NM–104–AD; Amendment 2015–8137. 700 airplanes. The MCAI states:
39–18561; AD 2016–12–12] * * * [T]he FAA published Special
Examining the AD Docket
RIN 2120–AA64 Federal Aviation Regulation (SFAR) 88, and
You may examine the AD docket on the Joint Aviation Authorities (JAA)
Airworthiness Directives; Fokker the Internet at http:// published Interim Policy INT/POL/25/12.
www.regulations.gov by searching for The review conducted by Fokker Services on
Services B.V. Airplanes the Fokker F27 design in response to these
and locating Docket No. FAA–2015–
AGENCY: Federal Aviation 8137; or in person at the Docket regulations identified a number of Fuel
Airworthiness Limitation Items (ALI) and
Administration (FAA), Department of Management Facility between 9 a.m. Critical Design Configuration Control
Transportation (DOT). and 5 p.m., Monday through Friday, Limitations (CDCCL) items to prevent the
ACTION: Final rule. except Federal holidays. The AD docket development of unsafe conditions within the
contains this AD, the regulatory fuel system.
SUMMARY: We are superseding evaluation, any comments received, and To introduce these Fuel ALI and CDCCL
Airworthiness Directive (AD) 2008–05– other information. The address for the items, Fokker Services published Service
18 R1 for certain Fokker Services B.V. Docket Office (telephone 800–647–5527) Bulletin (SB) F27/28–070. Consequently,
Model F.27 Mark 050, 200, 300, 400, is Docket Management Facility, U.S. EASA issued AD 2006–0207, requiring the
500, 600, and 700 airplanes. AD 2008– implementation of these Fuel ALI and
Department of Transportation, Docket
CDCCL items. That [EASA] AD was later
05–18 R1 required revising the Operations, M–30, West Building revised to make reference to SBF27–28–
Airworthiness Limitations Section Ground Floor, Room W12–140, 1200 070R1 and to specify that the use of later SB
(ALS) of the Instructions for Continued New Jersey Avenue SE., Washington, revisions was acceptable.
Airworthiness to incorporate new DC 20590. In 2014, Fokker Services issued Revision 2
limitations for fuel tank systems. This FOR FURTHER INFORMATION CONTACT: Tom of SBF27–28–070 to update the Fuel ALI and
new AD requires a new maintenance or Rodriguez, Aerospace Engineer, CDCCL items and to consolidate Fuel ALI
inspection program revision to and CDCCL items contained in a number of
International Branch, ANM–116,
incorporate the revised Airworthiness other SBs. Consequently, EASA issued AD
Transport Airplane Directorate, FAA, 2014–0105, superseding AD 2006–0207R1
Limitation Items (ALIs) and critical 1601 Lind Avenue SW., Renton, WA and requiring the implementation of the
design configuration control limitations 98057–3356; telephone 425–227–1137; updated Fuel ALI and CDCCL items.
(CDCCLs). This new AD also adds fax 425–227–1149. Since that [EASA] AD was issued, Fokker
certain airplanes to the applicability. Services issued Revision 3 of SBF27–28–070,
SUPPLEMENTARY INFORMATION:
This AD was prompted by the issuance primarily to introduce 2 additional CDCCL
of revised service information to update Discussion items.
the Fuel ALIs and CDCCLs that address We issued a notice of proposed For the reason described above, this
fuel tank system ignition sources. We [EASA] AD retains the requirements of EASA
rulemaking (NPRM) to amend 14 CFR AD 2014–0105, which is superseded, and
are issuing this AD to prevent the part 39 to supersede AD 2008–05–18 R1,
potential of ignition sources inside fuel requires implementation of the updated Fuel
Amendment 39–16083 (74 FR 57402, ALI and CDCCL items.
tanks, which, in combination with November 6, 2009) (‘‘AD 2008–05–18 More information on this subject can be
flammable fuel vapors, could result in R1’’). AD 2008–05–18 R1 applied to found in Fokker Services All Operators
fuel tank explosions and consequent certain Model F.27 Mark 050, 200, 300, Message AOF27.043#05.
loss of the airplane. 400, 500, 600, and 700 airplanes. The The unsafe condition is the potential
DATES: This AD becomes effective July NPRM published in the Federal of ignition sources inside fuel tanks.
22, 2016. Register on January 4, 2016 (81 FR 38) Such ignition sources, in combination
The Director of the Federal Register (‘‘the NPRM’’). The NPRM was with flammable fuel vapors, could result
approved the incorporation by reference prompted by the issuance of revised in fuel tank explosions and consequent
of a certain publication listed in this AD service information to update the Fuel loss of the airplane. You may examine
as of July 22, 2016. ALIs and CDCCLs that address fuel tank the MCAI in the AD docket on the
The Director of the Federal Register system ignition sources. The NPRM Internet at http://www.regulations.gov
approved the incorporation by reference proposed to retain the requirements of by searching for and locating it in
ehiers on DSK5VPTVN1PROD with RULES
of a certain publication listed in this AD AD 2008–05–18 R1, and require a new Docket No. FAA–2015–8137.
as of November 23, 2009 (74 FR 57402, maintenance or inspection program
November 6, 2009). revision to incorporate the revised ALIs Comments
ADDRESSES: For service information and CDCCLs. The NPRM also proposed We gave the public the opportunity to
identified in this final rule, contact to add certain airplanes to the participate in developing this AD. We
Fokker Services B.V., Technical applicability. We are issuing this AD to received no comments on the NPRM or
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Document Created: 2016-06-17 01:04:57
Document Modified: 2016-06-17 01:04:57
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective July 22, 2016. | |
| Contact | Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6501; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 39547 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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