80 FR 30605 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 103 (May 29, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 103 (May 29, 2015)
| Page Range | 30605-30608 | |
| FR Document | 2015-12858 |
[Federal Register Volume 80, Number 103 (Friday, May 29, 2015)] [Rules and Regulations] [Pages 30605-30608] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-12858] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations [[Page 30605]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0756; Directorate Identifier 2014-NM-103-AD; Amendment 39-18167; AD 2015-11-04] 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 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of cracked midspar fittings on the inboard and outboard nacelle struts. This AD requires repetitive inspections for cracking of the inboard and outboard midspar fittings of the nacelle struts and of the torque bulkhead, midspar chords, drag fitting, and front spar support, and doing applicable related investigative and corrective actions; replacing the midspar fittings; and doing other specified actions. We are issuing this AD to detect and correct cracking in the midspar fittings of the inboard and outboard nacelle struts, which could result in the loss of the structural integrity of the midspar fitting. This condition could cause an unsafe separation of the engine and consequent wing fire. DATES: This AD is effective July 6, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 6, 2015. ADDRESSES: 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. 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://regulations.gov by searching for and locating Docket No. FAA-2014-0756. 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-2014- 0756; 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: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; 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 707 airplanes, and Model 720 and 720B series airplanes. The NPRM published in the Federal Register on November 13, 2014 (79 FR 67379). The NPRM was prompted by reports of cracked midspar fittings on the inboard and outboard nacelle struts. The NPRM proposed to require repetitive inspections for cracking of the inboard and outboard midspar fittings of the nacelle struts and of the torque bulkhead, midspar chords, drag fitting, and front spar support, and doing applicable related investigative and corrective actions; replacing the midspar fittings; and doing other specified actions. We are issuing this AD to detect and correct cracking in the midspar fittings of the inboard and outboard nacelle struts, which could result in the loss of the structural integrity of the midspar fitting. This condition could cause an unsafe separation of the engine and consequent wing fire. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 67379, November 13, 2014) and the FAA's response to each comment. Request To Extend the Compliance Time The Air Force Life Cycle Management Center (AFLCMC) at Robins Air Force Base, and the Massachusetts Institute of Technology Lincoln Laboratory Flight Facility (LLFF), requested that the compliance time proposed in the NPRM (79 FR 67379, November 13, 2014) be extended. AFLCMC asked that the grace period be extended from 18 months after the effective date of the AD to 24 months after the effective date of the AD. This commenter explained that its airplanes are scheduled for heavy maintenance visits every 24 months, and the 18-month grace period for the initial actions proposed in the NPRM would negatively impact airplane availability. In addition, the AFLCMC stated that there is a low quantity of kits available to replace the inboard and outboard midspar fittings with new parts, as proposed in paragraphs (g) and (h) of the NPRM (79 FR 67379, November 13, 2014). This commenter also noted that the kits are expensive and have long lead times, which could impact operators' schedules. We infer that the commenter is requesting that the compliance time proposed in the NPRM be lengthened to accommodate parts availability. LLFF's interpretation of the compliance time was that the compliance time was related to the date of the service bulletin. LLFF commented that operators would have a difficult time complying with the requirements proposed in the NPRM (79 FR 67379, November 13, 2014). We do not agree with the commenters' requests to extend the compliance time. [[Page 30606]] In developing an appropriate compliance time for this action, we considered not only the degree of urgency associated with addressing the subject unsafe condition, but the manufacturer's recommendation for an appropriate compliance time, the availability of required parts, and the practical aspect of installing the required modification within an interval of time that corresponds to the typical scheduled maintenance for the majority of affected operators. The supplier of the parts kits reports that the lead time for kit delivery is 12 months from the date an operator places an order. This final rule provides operators with a grace period of 18 months from the effective date of this AD, which we deem adequate for acquiring the midspar fitting kits, performing the inspection, accomplishing any necessary corrective actions, and replacing the midspar fittings. However, under the provisions of paragraph (k) of this AD, we may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed this final rule regarding this issue. Request To Clarify the Unsafe Condition Boeing requested that the unsafe condition statement in the NPRM (79 FR 67379, November 13, 2014) be revised. The NPRM stated ``This condition could cause an unsafe separation of the engine and consequent wing fire.'' Boeing commented that the word ``consequent'' implied that the end result would always be a wing fire. Boeing suggested that the wording be changed to ``This condition could cause an unsafe separation of the engine and potential fire.'' We do not agree to revise the unsafe condition statement in this final rule. Where the unsafe condition states ``could result'' it is recognized that the loss of structural integrity, unsafe separation of the engine, and wing fire are possible outcomes in a chain of events. Furthermore, we frequently use ``consequent'' in unsafe condition statements when we state the end-level effect of the unsafe condition on an airplane. We have not changed this AD regarding this issue. Request To Revise the Discussion Section of the NPRM (79 FR 67379, November 13, 2014) Boeing requested that the term limit of validity (LOV) in the first paragraph of the Discussion section of the preamble of the NPRM (79 FR 67379, November 13, 2014) be removed because it is misleading. Boeing commented that the term LOV has implications associated with it which may not be intended. Boeing suggested that the term ``service objective'' be used instead of LOV. We agree that the unsafe condition addressed by this final rule is not related to an airplane reaching its LOV. The actions in this final rule are necessary to prevent loss of the structural integrity of the midspar fitting as the result of stress corrosion and fatigue at the lug and fatigue at the tangs. These actions do not directly support an airplane reaching its LOV. The Discussion section from the preamble of an NPRM is not repeated in a final rule so no change is necessary. We have revised paragraph (e) of this AD by removing the statement ``This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program.'' We replaced that statement with ``This AD was prompted by reports of cracked midspar fittings on the inboard and outboard nacelle struts.'' Request To Clarify Replacement Requirements Rafael Veas stated that two midspar fittings had already been replaced on an airplane at his facility. This commenter asked if all four midspar fittings have to be replaced, or only the two remaining midspar fittings that have not yet been replaced. We agree to clarify the replacement requirements of this final rule. Paragraph (f) of this AD states ``Comply with this AD within the compliance times specified, unless already done.'' The two midspar fittings that have already been replaced do not have to be replaced again if they have been replaced in accordance with the procedures mandated by this AD. For these two midspar fittings the repetitive inspection and replacement intervals should be calculated from the most recent midspar fitting replacement. We have not changed this final rule regarding this issue. Request To Revise the Cost Estimate The AFLCMC mentioned that the cost and labor estimates presented in the preamble of the NPRM (79 FR 67379, November 13, 2014) are significantly lower than the actual costs. The commenter stated that accomplishment of the actions proposed in the NPRM would require a set of ready-for-installation engine pylons, removal of all four engines, inspections, and reassembly, and the estimated cost would be over $1,000,000 per airplane. We infer that the commenter requested that the estimated costs be revised. After considering the data presented by the commenter, we agree that the cost and labor estimates referenced in the NPRM (79 FR 67379, November 13, 2014) are significantly lower than the actual costs. The cost estimate in the NPRM was for replacement of the midspar fitting for one engine, and the proposed requirement in the NPRM was for replacement of the midspar fitting for all four engines. The estimated cost information in this final rule has been revised to indicate this higher amount. We disagree, however, with the commenter's estimate that the cost will be over $1,000,000 per airplane. Our cost estimate includes the work hours and parts cost for the required midspar fitting replacements, but does not include costs associated with maintenance scheduling or a set of ready-for-installation engine pylons. 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 NPRM (79 FR 67379, November 13, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 67379, November 13, 2014). Related Service Information Under 1 CFR Part 51 We reviewed Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014. The service information describes procedures for repetitive inspections for cracking of the inboard and outboard midspar fittings of the nacelle struts and of the torque bulkhead, midspar chords, drag fitting, and front spar support, and related investigative and corrective actions; replacing the midspar fittings; and doing other specified actions. 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 of this AD. Costs of Compliance We estimate that this AD affects 12 airplanes of U.S. registry. [[Page 30607]] 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 ---------------------------------------------------------------------------------------------------------------- Inspections.................. 214 work-hours x $85 $0.................. $72,760 (4 pylons $873,120 per per hour = $18,190 per inspection inspection per pylon per cycle). cycle. inspection cycle. Replacement of midspar 18 work-hours x $85 Up to $7,867........ Up to $37,588 (1 Up to $451,056. fitting. per hour = $1,530 fitting per pylon, per pylon. 4 pylons total). Mid-interval inspections..... 107 work-hours x $85 $0.................. $36,380 (4 pylons $436,560 per per hour = $9,095 per inspection inspection per pylon per cycle). cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any additional inspections that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these inspections: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Inspections.............................. Up to 21 work-hours x $85 per hour $0 $1,785 = $1,785. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition corrective actions specified in this AD. 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): 2015-11-04 The Boeing Company: Amendment 39-18167; Docket No. FAA- 2014-0756; Directorate Identifier 2014-NM-103-AD. (a) Effective Date This AD is effective July 6, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 707-100 long body, -200, -100B long body, and -100B short body series airplanes; Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/ Pylons. (e) Unsafe Condition This AD was prompted by reports of cracked midspar fittings on the inboard and outboard nacelle struts. We are issuing this AD to detect and correct cracking in the midspar fittings of the inboard and outboard nacelle struts, which could result in the loss of the structural integrity of the midspar fitting. This condition could cause an unsafe separation of the engine and consequent wing fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections of Nacelle Struts and Surrounding Structure and Replacement of Inboard and Outboard Midspar Fittings At the applicable time specified in table 2 or table 3 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(1) of this AD: Do the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with part 2 or part 3, as applicable, of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by [[Page 30608]] paragraph (i)(2) of this AD. Before further flight, do all applicable related investigative and corrective actions, replace the inboard and outboard midspar fittings with new parts, and do other specified actions (including installing new bushings and oversize fasteners), in accordance with part 2 or part 3, as applicable, of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(2) of this AD. Repeat the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the applicable intervals specified in table 2 or table 3 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(1) of this AD. (1) A detailed inspection and a high frequency eddy current inspection (HFEC) for cracks in the inboard and outboard midspar fittings of the nacelle struts. (2) Open hole HFEC inspections for cracks in the torque bulkhead, midspar chords, drag fitting, and front spar support. (3) A surface HFEC inspection of the front spar support for cracks. (h) Mid-Interval Inspections and Replacement of Nacelle Strut Midspar Fittings At the applicable time specified in table 4 or 5 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014: Do the inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with part 4 or part 5, as applicable, of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative, corrective, and other specified actions (including installing new bushings and oversize fasteners) before further flight. Repeat the inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD thereafter at the applicable intervals specified in table 4 or 5 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014. The threshold for the repetitive inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD is 1,500 flight cycles or 48 months, whichever occurs first, since the most recent midspar fitting replacement. (1) A detailed inspection and a surface HFEC inspection for cracks in the inboard and outboard midspar fittings of the nacelle struts. (2) An open hole HFEC inspection for cracks in the drag fitting and front spar support. (3) A surface HFEC inspection for cracks in the front spar support. (i) Exceptions to Service Information Specifications (1) Where Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, specifies a compliance time ``after the Revision 6 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, specifies to contact Boeing for appropriate action: Do corrective actions before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Special Flight Permit Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (l) 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 required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. (l) Related Information For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5239; fax: 562-627-5210; email: [email protected]. (m) 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 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014. (ii) Reserved. (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. 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. (4) 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. (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 May 20, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-12858 Filed 5-28-15; 8:45 am] BILLING CODE 4910-13-P
![30605
Rules and Regulations Federal Register
Vol. 80, No. 103
Friday, May 29, 2015
This section of the FEDERAL REGISTER MC 2H–65, Seattle, WA 98124–2207; midspar fittings; and doing other
contains regulatory documents having general telephone 206–544–5000, extension 1; specified actions. We are issuing this
applicability and legal effect, most of which fax 206–766–5680; Internet https:// AD to detect and correct cracking in the
are keyed to and codified in the Code of www.myboeingfleet.com. You may view midspar fittings of the inboard and
Federal Regulations, which is published under this referenced service information at outboard nacelle struts, which could
50 titles pursuant to 44 U.S.C. 1510.
the FAA, Transport Airplane result in the loss of the structural
The Code of Federal Regulations is sold by Directorate, 1601 Lind Avenue SW., integrity of the midspar fitting. This
the Superintendent of Documents. Prices of Renton, WA. For information on the condition could cause an unsafe
new books are listed in the first FEDERAL availability of this material at the FAA, separation of the engine and consequent
REGISTER issue of each week. call 425–227–1221. It is also available wing fire.
on the Internet at http://regulations.gov Comments
by searching for and locating Docket No.
DEPARTMENT OF TRANSPORTATION FAA–2014–0756. We gave the public the opportunity to
participate in developing this AD. The
Federal Aviation Administration Examining the AD Docket following presents the comments
You may examine the AD docket on received on the NPRM (79 FR 67379,
14 CFR Part 39 the Internet at http:// November 13, 2014) and the FAA’s
[Docket No. FAA–2014–0756; Directorate www.regulations.gov by searching for response to each comment.
Identifier 2014–NM–103–AD; Amendment and locating Docket No. FAA–2014– Request To Extend the Compliance
39–18167; AD 2015–11–04] 0756; or in person at the Docket Time
RIN 2120–AA64
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday, The Air Force Life Cycle Management
except Federal holidays. The AD docket Center (AFLCMC) at Robins Air Force
Airworthiness Directives; The Boeing Base, and the Massachusetts Institute of
Company Airplanes contains this AD, the regulatory
evaluation, any comments received, and Technology Lincoln Laboratory Flight
AGENCY: Federal Aviation other information. The address for the Facility (LLFF), requested that the
Administration (FAA), DOT. Docket Office (phone: 800–647–5527) is compliance time proposed in the NPRM
(79 FR 67379, November 13, 2014) be
ACTION: Final rule. Docket Management Facility, U.S.
extended. AFLCMC asked that the grace
Department of Transportation, Docket
SUMMARY: We are adopting a new period be extended from 18 months
Operations, M–30, West Building
airworthiness directive (AD) for all The after the effective date of the AD to 24
Ground Floor, Room W12–140, 1200
Boeing Company Model 707 airplanes, months after the effective date of the
New Jersey Avenue SE., Washington,
and Model 720 and 720B series AD. This commenter explained that its
DC 20590.
airplanes. This AD was prompted by airplanes are scheduled for heavy
FOR FURTHER INFORMATION CONTACT: maintenance visits every 24 months,
reports of cracked midspar fittings on Chandra Ramdoss, Aerospace Engineer,
the inboard and outboard nacelle struts. and the 18-month grace period for the
Airframe Branch, ANM–120L, FAA, Los initial actions proposed in the NPRM
This AD requires repetitive inspections Angeles Aircraft Certification Office
for cracking of the inboard and outboard would negatively impact airplane
(ACO), 3960 Paramount Boulevard, availability.
midspar fittings of the nacelle struts and Lakewood, CA 90712–4137; phone:
of the torque bulkhead, midspar chords, In addition, the AFLCMC stated that
562–627–5239; fax: 562–627–5210; there is a low quantity of kits available
drag fitting, and front spar support, and email: chandraduth.ramdoss@faa.gov.
doing applicable related investigative to replace the inboard and outboard
and corrective actions; replacing the SUPPLEMENTARY INFORMATION: midspar fittings with new parts, as
midspar fittings; and doing other proposed in paragraphs (g) and (h) of
Discussion
specified actions. We are issuing this the NPRM (79 FR 67379, November 13,
We issued a notice of proposed 2014). This commenter also noted that
AD to detect and correct cracking in the rulemaking (NPRM) to amend 14 CFR
midspar fittings of the inboard and the kits are expensive and have long
part 39 by adding an AD that would lead times, which could impact
outboard nacelle struts, which could apply to all The Boeing Company Model
result in the loss of the structural operators’ schedules. We infer that the
707 airplanes, and Model 720 and 720B commenter is requesting that the
integrity of the midspar fitting. This series airplanes. The NPRM published
condition could cause an unsafe compliance time proposed in the NPRM
in the Federal Register on November 13, be lengthened to accommodate parts
separation of the engine and consequent 2014 (79 FR 67379). The NPRM was
wing fire. availability.
prompted by reports of cracked midspar LLFF’s interpretation of the
DATES: This AD is effective July 6, 2015. fittings on the inboard and outboard compliance time was that the
The Director of the Federal Register nacelle struts. The NPRM proposed to compliance time was related to the date
approved the incorporation by reference require repetitive inspections for of the service bulletin. LLFF commented
Lhorne on DSK2VPTVN1PROD with RULES
of a certain publication listed in this AD cracking of the inboard and outboard that operators would have a difficult
as of July 6, 2015. midspar fittings of the nacelle struts and time complying with the requirements
ADDRESSES: For service information of the torque bulkhead, midspar chords, proposed in the NPRM (79 FR 67379,
identified in this AD, contact Boeing drag fitting, and front spar support, and November 13, 2014).
Commercial Airplanes, Attention: Data doing applicable related investigative We do not agree with the commenters’
& Services Management, P.O. Box 3707, and corrective actions; replacing the requests to extend the compliance time.
VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\29MYR1.SGM 29MYR1](https://thefederalregister.org/doc/80_FR_30708/page/1.svg)
![Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations 30607
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
Inspections ............ 214 work-hours × $85 per hour = $0 ..................... $72,760 (4 pylons per inspection cycle) $873,120 per in-
$18,190 per pylon per inspection spection cycle.
cycle.
Replacement of 18 work-hours × $85 per hour = $1,530 Up to $7,867 ..... Up to $37,588 (1 fitting per pylon, 4 py- Up to $451,056.
midspar fitting. per pylon. lons total).
Mid-interval inspec- 107 work-hours × $85 per hour = $0 ..................... $36,380 (4 pylons per inspection cycle) $436,560 per in-
tions. $9,095 per pylon per inspection cycle. spection cycle.
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any additional inspections that would inspections. We have no way of might need these inspections:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Inspections ................ Up to 21 work-hours × $85 per hour = $1,785 ............................................................... $0 $1,785
We have received no definitive data (1) Is not a ‘‘significant regulatory (b) Affected ADs
that would enable us to provide cost action’’ under Executive Order 12866, None.
estimates for the on-condition corrective (2) Is not a ‘‘significant rule’’ under (c) Applicability
actions specified in this AD. DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), This AD applies to all The Boeing
Authority for This Rulemaking Company Model 707–100 long body, –200,
(3) Will not affect intrastate aviation –100B long body, and –100B short body
Title 49 of the United States Code in Alaska, and series airplanes; Model 707–300, –300B,
specifies the FAA’s authority to issue (4) Will not have a significant –300C, and –400 series airplanes; and Model
rules on aviation safety. Subtitle I, economic impact, positive or negative, 720 and 720B series airplanes; certificated in
section 106, describes the authority of on a substantial number of small entities any category.
the FAA Administrator. Subtitle VII: under the criteria of the Regulatory (d) Subject
Aviation Programs, describes in more Flexibility Act.
detail the scope of the Agency’s Air Transport Association (ATA) of
List of Subjects in 14 CFR Part 39 America Code 54, Nacelles/Pylons.
authority.
We are issuing this rulemaking under Air transportation, Aircraft, Aviation (e) Unsafe Condition
the authority described in Subtitle VII, safety, Incorporation by reference, This AD was prompted by reports of
Part A, Subpart III, Section 44701: Safety. cracked midspar fittings on the inboard and
‘‘General requirements.’’ Under that outboard nacelle struts. We are issuing this
section, Congress charges the FAA with Adoption of the Amendment AD to detect and correct cracking in the
promoting safe flight of civil aircraft in midspar fittings of the inboard and outboard
Accordingly, under the authority nacelle struts, which could result in the loss
air commerce by prescribing regulations delegated to me by the Administrator, of the structural integrity of the midspar
for practices, methods, and procedures the FAA amends 14 CFR part 39 as fitting. This condition could cause an unsafe
the Administrator finds necessary for follows: separation of the engine and consequent
safety in air commerce. This regulation wing fire.
is within the scope of that authority PART 39—AIRWORTHINESS
(f) Compliance
because it addresses an unsafe condition DIRECTIVES
that is likely to exist or develop on Comply with this AD within the
products identified in this rulemaking ■ 1. The authority citation for part 39 compliance times specified, unless already
continues to read as follows: done.
action.
Authority: 49 U.S.C. 106(g), 40113, 44701. (g) Inspections of Nacelle Struts and
Regulatory Findings Surrounding Structure and Replacement of
This AD will not have federalism § 39.13 [Amended] Inboard and Outboard Midspar Fittings
implications under Executive Order ■ 2. The FAA amends § 39.13 by adding At the applicable time specified in table 2
13132. This AD will not have a or table 3 of paragraph 1.E., ‘‘Compliance,’’
the following new airworthiness of Boeing 707 Alert Service Bulletin A3183,
substantial direct effect on the States, on directive (AD):
the relationship between the national Revision 6, dated February 7, 2014, except as
Lhorne on DSK2VPTVN1PROD with RULES
2015–11–04 The Boeing Company: required by paragraph (i)(1) of this AD: Do
government and the States, or on the
Amendment 39–18167; Docket No. the inspections required by paragraphs (g)(1),
distribution of power and (g)(2), and (g)(3) of this AD, in accordance
FAA–2014–0756; Directorate Identifier
responsibilities among the various 2014–NM–103–AD. with part 2 or part 3, as applicable, of the
levels of government. Accomplishment Instructions of Boeing 707
For the reasons discussed above, I (a) Effective Date Alert Service Bulletin A3183, Revision 6,
certify that this AD: This AD is effective July 6, 2015. dated February 7, 2014, except as required by
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![30608 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations
paragraph (i)(2) of this AD. Before further (2) Where Boeing 707 Alert Service information on the availability of this
flight, do all applicable related investigative Bulletin A3183, Revision 6, dated February 7, material at the FAA, call 425–227–1221.
and corrective actions, replace the inboard 2014, specifies to contact Boeing for (4) You may view this referenced service
and outboard midspar fittings with new appropriate action: Do corrective actions information at the FAA, Transport Airplane
parts, and do other specified actions before further flight using a method approved Directorate, 1601 Lind Avenue SW., Renton,
(including installing new bushings and in accordance with the procedures specified WA. For information on the availability of
oversize fasteners), in accordance with part 2 in paragraph (k) of this AD. this material at the FAA, call 425–227–1221.
or part 3, as applicable, of the (5) You may view this service information
Accomplishment Instructions of Boeing 707 (j) Special Flight Permit that is incorporated by reference at the
Alert Service Bulletin A3183, Revision 6, Special flight permits, as described in National Archives and Records
dated February 7, 2014, except as required by Section 21.197 and Section 21.199 of the Administration (NARA). For information on
paragraph (i)(2) of this AD. Repeat the Federal Aviation Regulations (14 CFR 21.197 the availability of this material at NARA, call
inspections required by paragraphs (g)(1), and 21.199), are not allowed. 202–741–6030, or go to: http://
(g)(2), and (g)(3) of this AD thereafter at the www.archives.gov/federal-register/cfr/ibr-
applicable intervals specified in table 2 or (k) Alternative Methods of Compliance locations.html.
table 3 of paragraph 1.E., ‘‘Compliance,’’ of (AMOCs)
Boeing 707 Alert Service Bulletin A3183, Issued in Renton, Washington, on May 20,
(1) The Manager, Los Angeles Aircraft 2015.
Revision 6, dated February 7, 2014, except as Certification Office (ACO), FAA, has the
required by paragraph (i)(1) of this AD. John P. Piccola, Jr.,
authority to approve AMOCs for this AD, if
(1) A detailed inspection and a high requested using the procedures found in 14 Acting Manager, Transport Airplane
frequency eddy current inspection (HFEC) for CFR 39.19. In accordance with 14 CFR 39.19, Directorate, Aircraft Certification Service.
cracks in the inboard and outboard midspar send your request to your principal inspector [FR Doc. 2015–12858 Filed 5–28–15; 8:45 am]
fittings of the nacelle struts. or local Flight Standards District Office, as BILLING CODE 4910–13–P
(2) Open hole HFEC inspections for cracks appropriate. If sending information directly
in the torque bulkhead, midspar chords, drag
to the manager of the ACO, send it to the
fitting, and front spar support.
attention of the person identified in DEPARTMENT OF TRANSPORTATION
(3) A surface HFEC inspection of the front
paragraph (l) of this AD. Information may be
spar support for cracks.
emailed to: 9-ANM-LAACO-AMOC- Federal Aviation Administration
(h) Mid-Interval Inspections and Requests@faa.gov.
Replacement of Nacelle Strut Midspar (2) Before using any approved AMOC,
notify your appropriate principal inspector,
14 CFR Part 39
Fittings
At the applicable time specified in table 4 or lacking a principal inspector, the manager [Docket No. FAA–2014–0584; Directorate
or 5 of paragraph 1.E., ‘‘Compliance,’’ of of the local flight standards district office/ Identifier 2014–NM–092–AD; Amendment
Boeing 707 Alert Service Bulletin A3183, certificate holding district office. 39–18158; AD 2015–10–03]
Revision 6, dated February 7, 2014: Do the (3) An AMOC that provides an acceptable
level of safety may be used for any repair RIN 2120–AA64
inspections required by paragraphs (h)(1),
(h)(2), and (h)(3) of this AD, in accordance required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Airworthiness Directives; Airbus
with part 4 or part 5, as applicable, of the
Accomplishment Instructions of Boeing 707 Designation Authorization (ODA) that has Airplanes
Alert Service Bulletin A3183, Revision 6, been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
AGENCY: Federal Aviation
dated February 7, 2014, except as required by Administration (FAA), Department of
paragraph (i)(2) of this AD. Do all applicable method to be approved, the repair must meet
the certification basis of the airplane and the Transportation (DOT).
related investigative, corrective, and other
specified actions (including installing new approval must specifically refer to this AD. ACTION: Final rule.
bushings and oversize fasteners) before (l) Related Information
further flight. Repeat the inspections required SUMMARY: We are superseding
by paragraphs (h)(1), (h)(2), and (h)(3) of this For more information about this AD, Airworthiness Directive (AD) 2014–09–
AD thereafter at the applicable intervals contact Chandra Ramdoss, Aerospace 05, for certain Airbus Model A330–200
specified in table 4 or 5 of paragraph 1.E., Engineer, Airframe Branch, ANM–120L, and –300 series airplanes, and Model
‘‘Compliance,’’ of Boeing 707 Alert Service FAA, Los Angeles ACO, 3960 Paramount A340–200 and –300 series airplanes. AD
Bulletin A3183, Revision 6, dated February 7, Boulevard, Lakewood, CA 90712–4137;
2014–09–05 required repetitive
2014. The threshold for the repetitive phone: 562–627–5239; fax: 562–627–5210;
email: chandraduth.ramdoss@faa.gov. inspections of certain sidestay upper
inspections required by paragraphs (h)(1),
cardan pins of the main landing gear
(h)(2), and (h)(3) of this AD is 1,500 flight (m) Material Incorporated by Reference
cycles or 48 months, whichever occurs first, (MLG) and associated nuts and retainer
since the most recent midspar fitting (1) The Director of the Federal Register assemblies, and pin replacement if
replacement. approved the incorporation by reference necessary. This AD was prompted by a
(1) A detailed inspection and a surface (IBR) of the service information listed in this determination that a previously optional
HFEC inspection for cracks in the inboard paragraph under 5 U.S.C. 552(a) and 1 CFR measurement is necessary to address the
and outboard midspar fittings of the nacelle part 51.
identified unsafe condition. This new
struts. (2) You must use this service information
as applicable to do the actions required by AD continues to require a detailed
(2) An open hole HFEC inspection for inspection for visible chrome of each
cracks in the drag fitting and front spar this AD, unless the AD specifies otherwise.
support. (i) Boeing 707 Alert Service Bulletin affected MLG sidestay upper cardan pin,
(3) A surface HFEC inspection for cracks in A3183, Revision 6, dated February 7, 2014. associated nuts, and retainer assembly,
the front spar support. (ii) Reserved. and pin replacement if needed, and
(3) For service information identified in adds new requirements for measuring
(i) Exceptions to Service Information this AD, contact Boeing Commercial cardan pin clearance dimensions (gap
Specifications Airplanes, Attention: Data & Services check), doing corrective actions, and
Lhorne on DSK2VPTVN1PROD with RULES
(1) Where Boeing 707 Alert Service Management, P.O. Box 3707, MC 2H–65,
reporting all findings. We are issuing
Bulletin A3183, Revision 6, dated February 7, Seattle, WA 98124–2207; telephone 206–
2014, specifies a compliance time ‘‘after the 544–5000, extension 1; fax 206–766–5680; this AD to detect and correct migration
Revision 6 date of this service bulletin,’’ this Internet https://www.myboeingfleet.com. You of the sidestay upper cardan pin, which
AD requires compliance within the specified may view this referenced service information could result in disconnection of the
compliance time after the effective date of at the FAA, Transport Airplane Directorate, sidestay upper arm from the airplane
this AD. 1601 Lind Avenue SW., Renton, WA. For structure, and could result in a landing
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Document Created: 2015-12-15 15:31:10
Document Modified: 2015-12-15 15:31:10
| 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 6, 2015. | |
| Contact | Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 80 FR 30605 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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