81 FR 21716 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 71 (April 13, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 71 (April 13, 2016)
| Page Range | 21716-21720 | |
| FR Document | 2016-08359 |
[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)] [Rules and Regulations] [Pages 21716-21720] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08359] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3147; Directorate Identifier 2014-NM-094-AD; Amendment 39-18479; AD 2016-08-03] 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 all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. This AD requires an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. This AD also provides an optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane. DATES: This AD is effective May 18, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 18, 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-2015- 3147. 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-2015- 3147; 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: Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; fax: 425- 917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. The NPRM published in the Federal Register on August 25, 2015 (80 FR 51491) (``the NPRM''). The NPRM was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. The NPRM proposed to require an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. The proposed AD also provided an optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to [[Page 21717]] the flightcrew and passengers, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Benjamin Kerensa commented that he supports the NPRM. Request To Change Terminology Boeing requested that we change the phrase ``inboard flap of the main flap'' to ``main flap of the inboard flap assembly'' in paragraphs (g) and (h) of the proposed AD. Boeing stated that this would clarify the inspection location. We agree with the commenter's request for the reason provided by the commenter. We have revised paragraphs (g) and (h) of this AD accordingly. Request To Clarify Requirements of a Certain Terminating Action Boeing requested that we revise the terminating action specified in paragraph (k)(1) of the proposed AD. Boeing recommended that at the end of paragraph (k)(1) of the proposed AD, we add the following language, ``Prior to accomplishing this option, the inspections of paragraph (h) must be accomplished and no cracking must have been found during that inspection.'' Boeing commented that the bushing replacement is only a terminating action if the fitting has been verified to be crack free. We agree to clarify the terminating action. As specified in Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, if cracking is found during an inspection that is part of the terminating action, a fitting replacement must be done instead of the terminating action. In addition, Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, specifies that if corrosion cannot be removed during the terminating action, a fitting replacement must be done instead of the terminating action. Therefore, we have revised paragraph (k)(1) of this AD to specify that the terminating action is acceptable provided no cracking is found during any inspection specified in Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, and all corrosion has been removed. We have also clarified the terminating actions specified in paragraphs (h), (i), (j), (k)(1), (k)(2), and (k)(3) of this AD to specify the terminating actions apply only to that fitting on which the terminating action is done. In addition, we have clarified the actions specified in paragraphs (i)(3)(i), (i)(3)(ii), and (i)(3)(iii) of this AD by specifying the actions include doing all applicable related investigative actions. Also, we have clarified the actions specified in paragraphs (j)(1) and (j)(2) of this AD by specifying the actions include doing all applicable related investigative and corrective actions. Request To Clarify Terminating Action Is an Option to the Inspections Boeing and American Airlines (AA) requested that we clarify that the terminating action can be done instead of the inspections. AA commented to revise the terminating action paragraph to state the following: If any inboard flap of the main flap having an affected part number and serial number is found during the inspection required by paragraph (g) of this AD: Except as provided by paragraph (l) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, do the terminating action in paragraph (k)(1), (k)(2), or (k)(3) of this AD or do the inspections specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Special attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, until a terminating action in paragraph (k)(1), (k)(2), or (k)(3) of this AD is done. AA commented that this change would align the proposed rule with paragraph 1.E., ``Compliance,'' table 1 and table 2, of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. AA also stated that this would clearly indicate that the terminating action would preclude having to accomplish first the initial inspection requirement in paragraph (h) of the proposed AD. Boeing requested that we add a sentence to the end of paragraph (h) to specify that the inspections are not required for any affected inboard flap assembly where one of the terminating actions specified in paragraph (k)(1), (k)(2), or (k)(3) of the proposed AD have been done. We agree with the commenters' request. We have revised paragraph (h) of this AD to clarify that the terminating actions may preclude the initial inspections because rework or replacement of the parts prevent the unsafe condition. Request To Clarify the Applicability Delta Airlines (DAL) requested that we clarify whether paragraph (c) of the proposed AD is intended for all Model 777-200, -200LR, -300, and -300ER series airplanes, or all Model 777-200, -200LR, -300 and - 300ER series airplanes, identified as Groups 1, 2, and 4 airplanes in Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. DAL stated that paragraph (c) of the proposed AD does not contain Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, to identify the airplane's applicability for the proposed AD. DAL commented that in the proposed rule under ``Differences Between This Proposed AD and the Service Information,'' the airplane's applicability is stated. DAL also stated that the same paragraph states that the proposed AD is applicable only to Groups 1, 2, and 4 airplanes (Model 777-200, -200LR, -300 and -300ER series airplanes) specified in Boeing Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. DAL commented that a review of the ``Compliance'' paragraph in the service information indicates that the FAA will possibly release an AD for airplanes in Groups 1, 2, and 4. We agree with the commenter's request to clarify the applicability of this AD. This AD applies to all Model 777-200, -200LR, -300, and - 300ER series airplanes as specified in paragraph (c) of this AD. The description of Groups 1, 2, and 4 airplanes in section 1.A., ``Effectivity,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, specifies Model 777-200, - 200LR, -300, and -300ER series airplanes. Additionally, as noted in the service information, the table of variable numbers given in section 1.A., ``Effectivity,'' only reflects up to line number 1322, and affected airplanes after line number 1322 will be added to the profile page of MyBoeingFleet.com. Therefore, this AD applies to all Model 777- 200, -200LR, -300, and -300ER series airplanes. We have not changed this AD 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: [[Page 21718]]Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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 Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. The service information describes procedures for an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. The service information also describes an optional terminating action for the repetitive inspections. 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 148 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection to determine the part 3 work-hours x $85 $0 $255................ $37,740. number. per hour = $255. Additional Inspections........... Up to 7 0 Up to $595, per Up to $88,060, per work[dash]hours x cycle. cycle. $85 per hour = $595, per cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that will be required based on the results of the inspection. The nested bushing installation of the attach fitting and the fitting replacement are also optional terminating actions. We have no way of determining the number of aircraft on which these actions might be done. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Nested bushing installation of the attach 40 work-hours x $85 per hour = $45 $3,445. fitting. $3,400. Fitting replacement........................... 73 work-hours x $85 per hour = 7,400 13,605. $6,205. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, all 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): 2016-08-03 The Boeing Company: Amendment 39-18479; Docket No. FAA- 2015-3147; Directorate Identifier 2014-NM-094-AD. (a) Effective Date This AD is effective May 18, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes, certificated in any category. [[Page 21719]] (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine the Part Number At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, except as provided by paragraph (l) of this AD: Do an inspection of the main flap of the inboard flap assembly for affected part and serial numbers, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the inboard flap can be conclusively determined from that review. (h) Additional Inspections If any main flap of the inboard flap assembly having an affected part number and serial number is found during the inspection required by paragraph (g) of this AD: Except as provided by paragraph (l) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do the terminating action specified in paragraph (k)(1), (k)(2), or (k)(3) of this AD, or do the inspections specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, until a terminating action in paragraph (k)(1), (k)(2), or (k)(3) of this AD is done. Accomplishing a terminating action specified in paragraph (k)(1), (k)(2), or (k)(3) of this AD terminates the inspections required by this paragraph for that fitting only. (1) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and a high frequency eddy current inspection for cracking, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014. (2) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and an ultrasound inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (i) Corrective Action for Bushing Migration If any bushing migration but no cracking is found during any inspection required by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do the actions specified in paragraphs (i)(1) through (i)(3) of this AD. Accomplishment of a terminating action specified in paragraph (i)(3) or (k) of this AD terminates the actions required by this paragraph for that fitting only. (1) Apply corrosion inhibiting compound BMS 3-23, Type II, around the bushing flanges on each side of the fitting, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. Re-apply the corrosion inhibiting compound at the time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (2) Repeat the inspections specified in paragraph (h)(1) or (h)(2) of this AD, except inspect for cracking only. (3) Do a terminating action specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD. (i) Install a nested bushing to the forward attach fitting of the aft flap track of the inboard flap, including doing all applicable related investigative actions, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (ii) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, including doing all applicable related investigative actions, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (iii) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, including doing all applicable related investigative actions, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (j) Corrective Actions for Cracking If any cracking is found during any inspection required by paragraph (h) or (i)(3) of this AD: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do a terminating action specified in paragraph (j)(1) or (j)(2) of this AD. Replacement of the forward attach fitting as specified in paragraph (j)(1) or (j)(2) of this AD terminates the actions in this AD for that fitting only. (1) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, including doing all applicable related investigative and corrective actions, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (2) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, including doing all applicable related investigative and corrective actions, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (k) Optional Terminating Actions (1) Installation of the nested bushing to the forward attach fitting of the aft flap track of the inboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD for that fitting only, provided no cracking is found during any inspection specified in Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, and all corrosion has been removed. (2) Replacement of the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD for that fitting only. (3) Replacement of the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD for that fitting only. (l) Exception to the Service Information Where Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (m) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraphs (h)(1) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777-57-0094, dated January 29, 2014, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Multi Operator Message MOM-MOM-13- [[Page 21720]] 0137-01B, dated February 21, 2013, which is not incorporated by reference in this AD. (n) 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 (o)(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. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(4)(i) and (n)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (o) Related Information (1) For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917- 6412; 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 (p)(3) and (p)(4) of this AD. (p) 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 Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (ii) Reserved. (3) For Boeing 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. Issued in Renton, Washington, on March 31, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08359 Filed 4-12-16; 8:45 am] BILLING CODE 4910-13-P
![21716 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
Worth, TX 76177; telephone (817) 222–5110; Issued in Fort Worth, Texas, on March 31, information at the FAA, Transport
email 9-ASW-FTW-AMOC-Requests@faa.gov. 2016. Airplane Directorate, 1601 Lind Avenue
(2) For operations conducted under a 14 James A. Grigg, SW., Renton, WA. For information on
CFR part 119 operating certificate or under Acting Manager, Rotorcraft Directorate, the availability of this material at the
14 CFR part 91, subpart K, we suggest that Aircraft Certification Service. FAA, call 425–227–1221. It is also
you notify your principal inspector, or
lacking a principal inspector, the manager of
[FR Doc. 2016–07979 Filed 4–12–16; 8:45 am] available on the Internet at http://
the local flight standards district office or BILLING CODE 4910–13–P www.regulations.gov by searching for
certificate holding district office, before and locating Docket No. FAA–2015–
operating any aircraft complying with this 3147.
AD through an AMOC. DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
(g) Additional Information Federal Aviation Administration You may examine the AD docket on
(1) Airbus Helicopters Alert Service the Internet at http://
Bulletin ASB No. SA341/SA342–05.40, 14 CFR Part 39 www.regulations.gov by searching for
Revision 0, dated April 28, 2014, which is and locating Docket No. FAA–2015–
not incorporated by reference, contains [Docket No. FAA–2015–3147; Directorate
Identifier 2014–NM–094–AD; Amendment 3147; or in person at the Docket
additional information about the subject of
this final rule. For Airbus Helicopters service 39–18479; AD 2016–08–03] Management Facility between 9 a.m.
information identified in this final rule, and 5 p.m., Monday through Friday,
RIN 2120–AA64
contact Airbus Helicopters, 2701 N. Forum except Federal holidays. The AD docket
Drive, Grand Prairie, TX 75052; telephone Airworthiness Directives; The Boeing contains this AD, the regulatory
(972) 641–0000 or (800) 232–0323; fax (972) Company Airplanes evaluation, any comments received, and
641–3775; or at http:// other information. The address for the
www.airbushelicopters.com/techpub. You AGENCY: Federal Aviation Docket Office (phone: 800–647–5527) is
may review a copy of the service information Administration (FAA), DOT. Docket Management Facility, U.S.
at the FAA, Office of the Regional Counsel, ACTION: Final rule. Department of Transportation, Docket
Southwest Region, 10101 Hillwood Pkwy, Operations, M–30, West Building
Room 6N–321, Fort Worth, TX 76177. SUMMARY: We are adopting a new Ground Floor, Room W12–140, 1200
(2) The subject of this AD is addressed in airworthiness directive (AD) for all The New Jersey Avenue SE., Washington,
European Aviation Safety Agency (EASA) AD
Boeing Company Model 777–200, DC 20590.
No. 2014–0216, dated September 24, 2014.
You may view the EASA AD on the Internet –200LR, –300, and –300ER series FOR FURTHER INFORMATION CONTACT: Eric
at http://www.regulations.gov in Docket No. airplanes. This AD was prompted by Lin, Aerospace Engineer, Airframe
FAA–2015–5914. reports of fractured forward attach Branch, ANM–120S, FAA, Seattle
fittings of the inboard flap outboard aft Aircraft Certification Office, 1601 Lind
(h) Subject flap track. The fractured fittings were Avenue SW., Renton, WA 98057–3356;
Joint Aircraft Service Component (JASC) determined to be the result of corrosion
Code: 6700, Main Rotor.
telephone: 425–917–6412; fax: 425–
pits forming on the inside diameter of 917–6590; email: Eric.Lin@faa.gov.
(i) Material Incorporated by Reference the fittings. This AD requires an
SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register inspection for the affected part number
approved the incorporation by reference of and serial number of the main flap; Discussion
the service information listed in this various additional repetitive inspections We issued a notice of proposed
paragraph under 5 U.S.C. 552(a) and 1 CFR of the fitting, if necessary; and rulemaking (NPRM) to amend 14 CFR
part 51. replacement of the fitting or nested part 39 by adding an AD that would
(2) You must use this service information bushing installation, if necessary, which
as applicable to do the actions required by
apply to all The Boeing Company Model
would terminate the inspections. This 777–200, –200LR, –300, and –300ER
this AD, unless the AD specifies otherwise. AD also provides an optional
(i) Gazelle Inspection—Check 65.12.607, series airplanes. The NPRM published
terminating action for the repetitive in the Federal Register on August 25,
‘‘Main Rotor Head: Torsion Tie-Back Check
inspections. We are issuing this AD to 2015 (80 FR 51491) (‘‘the NPRM’’). The
(Post MOD 076171),’’ dated August 2008, of
the Eurocopter Gazelle Helicopter detect and correct fracture of the fitting, NPRM was prompted by reports of
Maintenance Manual, Tome 1. which could result in the loss of the fractured forward attach fittings of the
(ii) Reserved. inboard aft flap and could lead to a inboard flap outboard aft flap track. The
(3) For Eurocopter service information punctured fuselage, causing injury to fractured fittings were determined to be
identified in this final rule, contact Airbus the flightcrew and passengers, and the result of corrosion pits forming on
Helicopters, 2701 N. Forum Drive, Grand damage to the airplane.
Prairie, TX 75052; telephone (972) 641–0000
the inside diameter of the fittings. The
DATES: This AD is effective May 18, NPRM proposed to require an
or (800) 232–0323; fax (972) 641–3775; or at
http://www.airbushelicopters.com/techpub.
2016. inspection for the affected part number
(4) You may view this service information The Director of the Federal Register and serial number of the main flap;
at FAA, Office of the Regional Counsel, approved the incorporation by reference various additional repetitive inspections
Southwest Region, 10101 Hillwood Pkwy, of a certain publication listed in this AD of the fitting, if necessary; and
Room 6N–321, Fort Worth, TX 76177. For as of May 18, 2016. replacement of the fitting or nested
information on the availability of this ADDRESSES: For service information bushing installation, if necessary, which
material at the FAA, call (817) 222–5110. identified in this final rule, contact would terminate the inspections. The
jstallworth on DSK7TPTVN1PROD with RULES
(5) You may view this service information Boeing Commercial Airplanes, proposed AD also provided an optional
that is incorporated by reference at the
National Archives and Records
Attention: Data & Services Management, terminating action for the repetitive
Administration (NARA). For information on P. O. Box 3707, MC 2H–65, Seattle, WA inspections. We are issuing this AD to
the availability of this material at NARA, call 98124–2207; telephone 206–544–5000, detect and correct fracture of the fitting,
(202) 741–6030, or go to: http:// extension 1; fax 206–766–5680; Internet which could result in the loss of the
www.archives.gov/federal-register/cfr/ibr- https://www.myboeingfleet.com. You inboard aft flap and could lead to a
locations.html. may view this referenced service punctured fuselage, causing injury to
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![21718 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
• Are consistent with the intent that Related Service Information Under 1 inspections. The service information
was proposed in the NPRM for CFR Part 51 also describes an optional terminating
correcting the unsafe condition; and action for the repetitive inspections.
We reviewed Boeing Special This service information is reasonably
• Do not add any additional burden Attention Service Bulletin 777–57–
upon the public than was already available because the interested parties
0094, Revision 1, dated November 5, have access to it through their normal
proposed in the NPRM. 2014. The service information describes course of business or by the means
We also determined that these procedures for an inspection for the identified in the ADDRESSES section.
changes will not increase the economic affected part number and serial number
burden on any operator or increase the of the main flap; various additional Costs of Compliance
scope of this AD. repetitive inspections of the fitting, if We estimate that this AD affects 148
necessary; and replacement of the fitting airplanes of U.S. registry.
or nested bushing installation, if We estimate the following costs to
necessary, which would terminate the comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection to determine the part 3 work-hours × $85 per hour = $255 $0 $255 .............................. $37,740.
number.
Additional Inspections ....................... Up to 7 work-hours × $85 per hour = 0 Up to $595, per cycle ... Up to $88,060, per
$595, per cycle. cycle.
We estimate the following costs to do inspection. The nested bushing terminating actions. We have no way of
any necessary replacements that will be installation of the attach fitting and the determining the number of aircraft on
required based on the results of the fitting replacement are also optional which these actions might be done.
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Nested bushing installation of the attach fitting ........... 40 work-hours × $85 per hour = $3,400 ..................... $45 $3,445.
Fitting replacement ...................................................... 73 work-hours × $85 per hour = $6,205 ..................... 7,400 13,605.
According to the manufacturer, all of products identified in this rulemaking Adoption of the Amendment
the costs of this AD may be covered action.
Accordingly, under the authority
under warranty, thereby reducing the Regulatory Findings delegated to me by the Administrator,
cost impact on affected individuals. We
This AD will not have federalism the FAA amends 14 CFR part 39 as
do not control warranty coverage for follows:
affected individuals. As a result, we implications under Executive Order
have included all costs in our cost 13132. This AD will not have a PART 39—AIRWORTHINESS
estimate. substantial direct effect on the States, on DIRECTIVES
the relationship between the national
Authority for This Rulemaking government and the States, or on the ■ 1. The authority citation for part 39
distribution of power and continues to read as follows:
Title 49 of the United States Code
responsibilities among the various
specifies the FAA’s authority to issue levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
rules on aviation safety. Subtitle I,
For the reasons discussed above, I § 39.13 [Amended]
section 106, describes the authority of certify that this AD:
the FAA Administrator. Subtitle VII: ■ 2. The FAA amends § 39.13 by adding
(1) Is not a ‘‘significant regulatory
Aviation Programs, describes in more action’’ under Executive Order 12866, the following new airworthiness
detail the scope of the Agency’s directive (AD):
(2) Is not a ‘‘significant rule’’ under
authority. 2016–08–03 The Boeing Company:
DOT Regulatory Policies and Procedures
We are issuing this rulemaking under (44 FR 11034, February 26, 1979), Amendment 39–18479; Docket No.
the authority described in Subtitle VII, (3) Will not affect intrastate aviation FAA–2015–3147; Directorate Identifier
Part A, Subpart III, Section 44701: 2014–NM–094–AD.
in Alaska, and
‘‘General requirements.’’ Under that (4) Will not have a significant (a) Effective Date
section, Congress charges the FAA with economic impact, positive or negative, This AD is effective May 18, 2016.
promoting safe flight of civil aircraft in on a substantial number of small entities
(b) Affected ADs
jstallworth on DSK7TPTVN1PROD with RULES
air commerce by prescribing regulations under the criteria of the Regulatory
for practices, methods, and procedures Flexibility Act. None.
the Administrator finds necessary for (c) Applicability
safety in air commerce. This regulation List of Subjects in 14 CFR Part 39
This AD applies to all The Boeing
is within the scope of that authority Air transportation, Aircraft, Aviation Company Model 777–200, –200LR, –300, and
because it addresses an unsafe condition safety, Incorporation by reference, –300ER series airplanes, certificated in any
that is likely to exist or develop on Safety. category.
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![21720 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
0137–01B, dated February 21, 2013, which is (i) Boeing Special Attention Service DATES: This AD is effective May 18,
not incorporated by reference in this AD. Bulletin 777–57–0094, Revision 1, dated 2016.
November 5, 2014. The Director of the Federal Register
(n) Alternative Methods of Compliance (ii) Reserved.
(AMOCs) approved the incorporation by reference
(3) For Boeing service information
(1) The Manager, Seattle Aircraft identified in this AD, contact Boeing
of a certain publication listed in this AD
Certification Office (ACO), FAA, has the Commercial Airplanes, Attention: Data & as of May 18, 2016.
authority to approve AMOCs for this AD, if Services Management, P. O. Box 3707, MC ADDRESSES: For service information
requested using the procedures found in 14 2H–65, Seattle, WA 98124–2207; telephone identified in this final rule, contact
CFR 39.19. In accordance with 14 CFR 39.19, 206–544–5000, extension 1; fax 206–766– Boeing Commercial Airplanes,
send your request to your principal inspector 5680; Internet https:// Attention: Data & Services Management,
or local Flight Standards District Office, as www.myboeingfleet.com. P.O. Box 3707, MC 2H–65, Seattle, WA
appropriate. If sending information directly (4) You may view this service information
98124–2207; telephone 206–544–5000,
to the manager of the ACO, send it to the at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For extension 1; fax 206–766–5680; Internet
attention of the person identified in
paragraph (o)(1) of this AD. Information may information on the availability of this https://www.myboeingfleet.com. You
be emailed to: 9-ANM-Seattle-ACO-AMOC- material at the FAA, call 425–227–1221. may view this referenced service
Requests@faa.gov. (5) You may view this service information information at the FAA, Transport
(2) Before using any approved AMOC, that is incorporated by reference at the Airplane Directorate, 1601 Lind Avenue
notify your appropriate principal inspector, National Archives and Records SW., Renton, WA. For information on
or lacking a principal inspector, the manager Administration (NARA). For information on the availability of this material at the
of the local flight standards district office/ the availability of this material at NARA, call FAA, call 425–227–1221. It is also
certificate holding district office. 202–741–6030, or go to: http://www.archives.
available on the Internet at http://
(3) An AMOC that provides an acceptable gov/federal-register/cfr/ibr-locations.html.
www.regulations.gov by searching for
level of safety may be used for any repair, Issued in Renton, Washington, on March and locating Docket No. FAA–2015–
modification, or alteration required by this 31, 2016. 2959.
AD if it is approved by the Boeing Victor Wicklund,
Commercial Airplanes Organization Acting Manager, Transport Airplane Examining the AD Docket
Designation Authorization (ODA) that has Directorate, Aircraft Certification Service. You may examine the AD docket on
been authorized by the Manager, Seattle
ACO, to make those findings. To be [FR Doc. 2016–08359 Filed 4–12–16; 8:45 am] the Internet at http://
approved, the repair method, modification BILLING CODE 4910–13–P www.regulations.gov by searching for
deviation, or alteration deviation must meet and locating Docket No. FAA–2015–
the certification basis of the airplane and the 2959; or in person at the Docket
approval must specifically refer to this AD. DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
(4) For service information that contains and 5 p.m., Monday through Friday,
steps that are labeled as Required for Federal Aviation Administration except Federal holidays. The AD docket
Compliance (RC), the provisions of contains this AD, the regulatory
paragraphs (n)(4)(i) and (n)(4)(ii) apply. 14 CFR Part 39 evaluation, any comments received, and
(i) The steps labeled as RC, including
[Docket No. FAA–2015–2959; Directorate
other information. The address for the
substeps under an RC step and any figures
identified in an RC step, must be done to Identifier 2015–NM–008–AD; Amendment Docket Office (phone: 800–647–5527) is
comply with the AD. An AMOC is required 39–18470; AD 2016–07–25] Docket Management Facility, U.S.
for any deviations to RC steps, including Department of Transportation, Docket
substeps and identified figures. RIN 2120–AA64 Operations, M–30, West Building
(ii) Steps not labeled as RC may be Ground Floor, Room W12–140, 1200
deviated from using accepted methods in Airworthiness Directives; The Boeing New Jersey Avenue SE., Washington,
accordance with the operator’s maintenance Company Airplanes DC 20590.
or inspection program without obtaining
AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT:
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can Administration (FAA), DOT. Sean J. Schauer, Aerospace Engineer,
still be done as specified, and the airplane ACTION: Final rule. Systems and Equipment Branch, ANM–
can be put back in an airworthy condition. 130S, FAA, Seattle Aircraft Certification
SUMMARY: We are adopting a new Office (ACO), 1601 Lind Avenue SW.,
(o) Related Information airworthiness directive (AD) for certain Renton, WA 98057–3356; phone: 425–
(1) For more information about this AD, The Boeing Company Model 787–8 917–6479; fax: 425–917–6590; email:
contact Eric Lin, Aerospace Engineer, airplanes. This AD was prompted by sean.schauer@faa.gov.
Airframe Branch, ANM–120S, FAA, Seattle reports indicating that the ram air SUPPLEMENTARY INFORMATION:
ACO, 1601 Lind Avenue SW., Renton, WA
turbine (RAT) assembly may fail to
98057–3356; telephone: 425–917–6412; fax: Discussion
425–917–6590; email: Eric.Lin@faa.gov. operate if deployed at low airspeeds.
(2) Service information identified in this This AD requires replacing either the We issued a notice of proposed
AD that is not incorporated by reference is RAT pump and control module rulemaking (NPRM) to amend 14 CFR
available at the addresses specified in assembly or the entire RAT assembly. part 39 by adding an AD that would
paragraphs (p)(3) and (p)(4) of this AD. We are issuing this AD to prevent apply to certain The Boeing Company
(p) Material Incorporated by Reference
failure of the RAT assembly to operate Model 787–8 airplanes. The NPRM
at low air speeds. The volume fuse on published in the Federal Register on
jstallworth on DSK7TPTVN1PROD with RULES
(1) The Director of the Federal Register the RAT assembly may be activated in- July 24, 2015 (80 FR 43972) (‘‘the
approved the incorporation by reference
(IBR) of the service information listed in this
flight before the RAT is deployed. This NPRM’’). The NPRM was prompted by
paragraph under 5 U.S.C. 552(a) and 1 CFR may lead to improper pump hydraulic reports indicating that the RAT
part 51. pressure offloading when the RAT is assembly may fail to operate if deployed
(2) You must use this service information needed. Failure of the RAT to operate in at low airspeeds. The NPRM proposed
as applicable to do the actions required by an all engine out event would result in to require replacing either the RAT
this AD, unless the AD specifies otherwise. loss of control of the airplane. pump and control module assembly or
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Document Created: 2016-04-13 03:11:52
Document Modified: 2016-04-13 03:11:52
| 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 May 18, 2016. | |
| Contact | Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; fax: 425- 917-6590; email: [email protected] | |
| FR Citation | 81 FR 21716 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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