Airworthiness Directives; The Boeing Company Airplanes, 21426-21429 [2012-8232]

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Download as PDF 21426 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations (k) Parts Installation As of the effective date of this AD, do not install any No. 2 or No. 3 window having P/ N 65B27042–( ), 65B27043–( ), 65B27046– ( ), or 65B27047–( ) that is not new or on which the window flight hours are not known, on any airplanes, unless the actions specified in paragraph (g) of this AD are done. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office, 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (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, Seattle 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. (4) AMOCs previously approved in accordance with AD 2007–15–10, Amendment 39–15139 (72 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007), are approved as AMOCs for the corresponding provisions of this AD except previous AMOCs approving window replacement that do not specify installing dual structural glass pane windows are not considered approved for corresponding inspection methods required by this AD. tkelley on DSK3SPTVN1PROD with RULES (m) Related Information For more information about this AD, contact Nathan P. Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on May 15, 2012. (i) Boeing Service Bulletin 747–56A2012, Revision 1, dated August 12, 2010. (4) The following service information was approved for IBR on September 4, 2007 (72 VerDate Mar<15>2010 16:37 Apr 09, 2012 Jkt 226001 FR 41438, July 30, 2007; as corrected by 72 FR 53923, September 21, 2007). (i) Boeing Alert Service Bulletin 747– 56A2012, dated August 24, 2006. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; phone: 206–544–5000, extension 1; fax: 206–766– 5680; email: me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. (6) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 23, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–8452 Filed 4–9–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0915; Directorate Identifier 2011–NM–020–AD; Amendment 39–17013; AD 2012–07–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747 airplanes. This AD was prompted by reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. This AD requires repetitive general visual inspections for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections for cracking of the latch pins; and corrective actions if necessary. We are issuing this AD to detect and correct fractured or broken latch pins, which SUMMARY: PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane. DATES: This AD is effective May 15, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 15, 2012. 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; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 Document 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 1, 2011 (76 FR 54405). That NPRM proposed to require repetitive general visual inspections for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections for cracking of the latch pins; and corrective actions if necessary. E:\FR\FM\10APR1.SGM 10APR1 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Request to Withdraw the NPRM (76 FR 54405, September 1, 2011) United Parcel Service (UPS) asked that we withdraw the NPRM (76 FR 54405, September 1, 2011). UPS stated that there is a lack of justification for issuing the NPRM and added that it is being issued based on a report of a fatigue crack in the 17–4PH material latch pins of the lower cargo door, and the assumption that adjacent latch pins could also be affected. UPS noted that the latching structures of the lower forward and aft cargo door each include eight latch pins; those latch pins are part of a fail-safe design, which should preclude critical failure with the failure of one element. UPS added that the Model 747–400 maintenance planning document includes a detailed inspection of the latch mechanism of the lower cargo door, which includes the latch pins, at 2 year or 2,000 flight cycle intervals, whichever occurs first. UPS noted that the NPRM would require repetitive inspections at 1,600flight-cycle intervals—a modest increase in frequency over the existing maintenance program—which has already been proven successful at detecting damage to adjacent latch pins. UPS concluded that, based on the extensive fleet history of the latch pins of these lower cargo doors, with no reports of adjacent pin failures, the existing maintenance program inspections of the latch pins are adequate. We do not agree with the commenter’s request to withdraw the NPRM (76 FR 54405, September 1, 2011). Although the commenter has not experienced pin failure in service, the manufacturer has found pin fatigue failure on another airplane of the same type design. Therefore, we find we must issue this AD to address the identified unsafe condition on the entire fleet. The inspections identified in the maintenance planning document are general visual inspections of the entire door. The inspections required by this final rule include detailed inspections of the latch pins themselves. These detailed inspections are the result of the pin fracturing in service. The fractured pin was the number eight latch pin on the lower sill of the aft lower lobe cargo door; investigation by the manufacturer revealed that the crack initiated due to fatigue, and propagated by a combination of fatigue and stress corrosion. If the latch pins on the lower sill are not regularly inspected, and broken latch pins are not replaced, the forward and/or aft cargo door could open during service, resulting in loss of the cargo door, rapid decompression, and significant damage to the airplane. No change to the AD is necessary in this regard. Request To Clarify Language in Relevant Service Information Section Boeing asked that the description specified in the ‘‘Relevant Service Information’’ section of the NPRM (76 FR 54405, September 1, 2011) be changed as follows: ‘‘The service bulletin describes procedures for repetitive detail inspections of latch pins for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections of the replaced latch pins for cracked, broken or missing latch pins; and corrective actions if necessary.’’ Boeing stated that Boeing Alert Service Bulletin 747– 53A2835, dated October 28, 2010, necessitates that a detailed inspection be done on all pins (including previously replaced pins). Boeing added that the detailed inspection is for cracks, and the general visual inspection is to look for the broken and missing pins. Boeing notes that paragraph (g) of the NPRM provides the correct description of the inspections specified in the service bulletin. We acknowledge the commenter’s concern and agree that the language could be clarified somewhat; however, since that section of the preamble does not reappear in the final rule, no change to this AD is necessary in this regard. Request To Include Revision 1 of the Referenced Service Bulletin Boeing also asked that Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011, be included 21427 in the NPRM (76 FR 54405, September 1, 2011) for accomplishing certain actions. Boeing Alert Service Bulletin 747–53A2835, dated October 28, 2010, was referred to as the appropriate source of service information for accomplishing the actions specified in the NPRM. Boeing added that Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011, is scheduled for FAA-approval, and includes a latch pin modification and post-modification inspection to address the safety issue. We have reviewed Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011, and agree to include it in this final rule as an additional source of service information. Boeing Alert Service Bulletin 747– 53A2835, Revision 1, dated December 8, 2011, reduces an existing compliance time, adds a latch pin modification, and repetitive post-modification inspections. We are including the actions in Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011, as optional in order to avoid delaying issuance of the AD. We have revised paragraph (g) of this AD accordingly. We are currently considering additional rulemaking to require the modification and post-modification inspections. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the 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 (76 FR 54405, September 1, 2011) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (76 FR 54405, September 1, 2011). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD affects 228 airplanes of U.S. registry. We estimate the following costs to comply with this AD: tkelley on DSK3SPTVN1PROD with RULES ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ...... 3 work-hours × $85 per hour = $255 per inspection cycle. $0 $255 per inspection cycle ..... VerDate Mar<15>2010 16:37 Apr 09, 2012 Jkt 226001 PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 E:\FR\FM\10APR1.SGM Cost on U.S. operators $58,140 per inspection cycle. 10APR1 21428 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations We estimate the following costs to do any necessary replacements/ modifications that would be required based on the results of the required inspection. We have no way of determining the number of aircraft that might need these actions: ON-CONDITION COSTS Action Labor cost Parts cost Replacement of latch pins .................. Modification of latch fittings ................ 8 work-hours × $85 per hour = $680 ............................................................. 36 hours × $85 per work-hours = $3,060 ...................................................... Authority for this Rulemaking Adoption of the Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: tkelley on DSK3SPTVN1PROD with RULES Regulatory Findings PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–07–07 The Boeing Company: Amendment 39–17013; Docket No. FAA–2011–0915; Directorate Identifier 2011–NM–020–AD. (a) Effective Date This AD is effective May 15, 2012. (b) Affected ADs 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. None. (c) Applicability This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes; certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53: Fuselage. (e) Unsafe Condition This AD was prompted by reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. We are issuing this AD to detect and correct fractured or broken latch pins, which could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane. List of Subjects in 14 CFR Part 39 (f) Compliance Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Comply with this AD within the compliance times specified, unless already done. VerDate Mar<15>2010 16:37 Apr 09, 2012 Jkt 226001 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 $0 0 Cost per product $680 3,060 (g) Inspections Before the accumulation of 6,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later: Do a general visual inspection for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors, and a detailed inspection for cracking of the latch pins, in accordance with paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 747–53A2835, dated October 28, 2010; or Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2835, dated October 28, 2010; or Boeing Alert Service Bulletin 747– 53A2835, Revision 1, dated December 8, 2011. Before further flight, do all applicable corrective actions, in accordance with paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 747–53A2835, dated October 28, 2010; or Boeing Alert Service Bulletin 747–53A2835, Revision 1, dated December 8, 2011. (h) Special Flight Permits Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the cabin is not pressurized. (i) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (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 ODA that has been authorized by the Manager, Seattle E:\FR\FM\10APR1.SGM 10APR1 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. (j) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; email: nathan.p.weigand@faa.gov. (k) Material Incorporated by Reference You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information. (1) Boeing Alert Service Bulletin 747– 53A2835, dated October 28, 2010. (2) Boeing Alert Service Bulletin 747– 53A2835, Revision 1, dated December 8, 2011. (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; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (4) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the 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 28, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–8232 Filed 4–9–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 tkelley on DSK3SPTVN1PROD with RULES [Docket No. FAA–2011–0025; Directorate Identifier 2010–NM–208–AD; Amendment 39–17012; AD 2012–07–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Mar<15>2010 16:37 Apr 09, 2012 Jkt 226001 ACTION: Discussion Final rule. We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a new revision to the airworthiness limitations of the maintenance planning document. This AD requires revising the maintenance program to update inspection requirements to detect fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes. SUMMARY: This AD is effective May 15, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 15, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 Document 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: James Sutherland, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6533; fax: (425) 917–6590; email: James.Sutherland@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00039 Fmt 4700 21429 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on January 19, 2011 (76 FR 3054). That NPRM proposed to require revising the maintenance program to update inspection requirements to detect fatigue cracking of principal structural elements (PSEs). Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (76 FR 3054, January 19, 2011) and the FAA’s response to each comment. Request To Refer to Latest Service Information Boeing and Japan Airlines (JAL) requested that we revise the NPRM (76 FR 3054, January 19, 2011) to refer to two new revisions of Section 9, ‘‘Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),’’ D622W001–9, of the Boeing 777 Maintenance Planning Data (MPD) Document, published after we issued the NPRM. Boeing stated that both revisions contain the same structures airworthiness limitations (AWL) data, but were revised for reasons that did not affect the data in Subsection B, Airworthiness Limitations—Structural Inspections of that document, which was specified in the NPRM. We agree with the request to refer to the later service information. We have changed this final rule to refer to Section 9, ‘‘Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),’’ D622W001–9, Revision July 2011, of the Boeing 777 Maintenance Planning Data (MPD) Document to this AD. (Section 9, ‘‘Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),’’ D622W001–9, Revision January 2010, of the Boeing 777 Maintenance Planning Data (MPD) Document was specified in the NPRM (76 FR 3054, January 19, 2011).) (Subsection B, Airworthiness Limitations—Structural Inspections, of Section 9, ‘‘Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),’’ D622W001–9, of the Boeing 777 Maintenance Planning Data (MPD) Document is identical to the January 2010 revision.) We have changed paragraph (g) in this final rule accordingly. E:\FR\FM\10APR1.SGM 10APR1

Agencies

[Federal Register Volume 77, Number 69 (Tuesday, April 10, 2012)]
[Rules and Regulations]
[Pages 21426-21429]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-8232]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0915; Directorate Identifier 2011-NM-020-AD; 
Amendment 39-17013; AD 2012-07-07]
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 747 airplanes. This AD was prompted by reports of 
fractured latch pins found in service; investigation revealed that the 
cracking and subsequent fracture were initiated by fatigue and 
propagated by a combination of fatigue and stress corrosion. This AD 
requires repetitive general visual inspections for broken or missing 
latch pins of the lower sills of the forward and aft lower lobe cargo 
doors; repetitive detailed inspections for cracking of the latch pins; 
and corrective actions if necessary. We are issuing this AD to detect 
and correct fractured or broken latch pins, which could result in a 
forward or aft lower lobe cargo door opening and detaching during 
flight, and consequent rapid decompression of the airplane.

DATES: This AD is effective May 15, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 15, 2012.

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; email me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 Document 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6428; fax: (425) 917-6590; email: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on September 1, 2011 
(76 FR 54405). That NPRM proposed to require repetitive general visual 
inspections for broken or missing latch pins of the lower sills of the 
forward and aft lower lobe cargo doors; repetitive detailed inspections 
for cracking of the latch pins; and corrective actions if necessary.

[[Page 21427]]

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Request to Withdraw the NPRM (76 FR 54405, September 1, 2011)

    United Parcel Service (UPS) asked that we withdraw the NPRM (76 FR 
54405, September 1, 2011). UPS stated that there is a lack of 
justification for issuing the NPRM and added that it is being issued 
based on a report of a fatigue crack in the 17-4PH material latch pins 
of the lower cargo door, and the assumption that adjacent latch pins 
could also be affected. UPS noted that the latching structures of the 
lower forward and aft cargo door each include eight latch pins; those 
latch pins are part of a fail-safe design, which should preclude 
critical failure with the failure of one element. UPS added that the 
Model 747-400 maintenance planning document includes a detailed 
inspection of the latch mechanism of the lower cargo door, which 
includes the latch pins, at 2 year or 2,000 flight cycle intervals, 
whichever occurs first. UPS noted that the NPRM would require 
repetitive inspections at 1,600-flight-cycle intervals--a modest 
increase in frequency over the existing maintenance program--which has 
already been proven successful at detecting damage to adjacent latch 
pins. UPS concluded that, based on the extensive fleet history of the 
latch pins of these lower cargo doors, with no reports of adjacent pin 
failures, the existing maintenance program inspections of the latch 
pins are adequate.
    We do not agree with the commenter's request to withdraw the NPRM 
(76 FR 54405, September 1, 2011). Although the commenter has not 
experienced pin failure in service, the manufacturer has found pin 
fatigue failure on another airplane of the same type design. Therefore, 
we find we must issue this AD to address the identified unsafe 
condition on the entire fleet.
    The inspections identified in the maintenance planning document are 
general visual inspections of the entire door. The inspections required 
by this final rule include detailed inspections of the latch pins 
themselves. These detailed inspections are the result of the pin 
fracturing in service. The fractured pin was the number eight latch pin 
on the lower sill of the aft lower lobe cargo door; investigation by 
the manufacturer revealed that the crack initiated due to fatigue, and 
propagated by a combination of fatigue and stress corrosion. If the 
latch pins on the lower sill are not regularly inspected, and broken 
latch pins are not replaced, the forward and/or aft cargo door could 
open during service, resulting in loss of the cargo door, rapid 
decompression, and significant damage to the airplane. No change to the 
AD is necessary in this regard.

Request To Clarify Language in Relevant Service Information Section

    Boeing asked that the description specified in the ``Relevant 
Service Information'' section of the NPRM (76 FR 54405, September 1, 
2011) be changed as follows: ``The service bulletin describes 
procedures for repetitive detail inspections of latch pins for broken 
or missing latch pins of the lower sills of the forward and aft lower 
lobe cargo doors; repetitive detailed inspections of the replaced latch 
pins for cracked, broken or missing latch pins; and corrective actions 
if necessary.'' Boeing stated that Boeing Alert Service Bulletin 747-
53A2835, dated October 28, 2010, necessitates that a detailed 
inspection be done on all pins (including previously replaced pins). 
Boeing added that the detailed inspection is for cracks, and the 
general visual inspection is to look for the broken and missing pins. 
Boeing notes that paragraph (g) of the NPRM provides the correct 
description of the inspections specified in the service bulletin.
    We acknowledge the commenter's concern and agree that the language 
could be clarified somewhat; however, since that section of the 
preamble does not reappear in the final rule, no change to this AD is 
necessary in this regard.

Request To Include Revision 1 of the Referenced Service Bulletin

    Boeing also asked that Boeing Alert Service Bulletin 747-53A2835, 
Revision 1, dated December 8, 2011, be included in the NPRM (76 FR 
54405, September 1, 2011) for accomplishing certain actions. Boeing 
Alert Service Bulletin 747-53A2835, dated October 28, 2010, was 
referred to as the appropriate source of service information for 
accomplishing the actions specified in the NPRM. Boeing added that 
Boeing Alert Service Bulletin 747-53A2835, Revision 1, dated December 
8, 2011, is scheduled for FAA-approval, and includes a latch pin 
modification and post-modification inspection to address the safety 
issue.
    We have reviewed Boeing Alert Service Bulletin 747-53A2835, 
Revision 1, dated December 8, 2011, and agree to include it in this 
final rule as an additional source of service information. Boeing Alert 
Service Bulletin 747-53A2835, Revision 1, dated December 8, 2011, 
reduces an existing compliance time, adds a latch pin modification, and 
repetitive post-modification inspections. We are including the actions 
in Boeing Alert Service Bulletin 747-53A2835, Revision 1, dated 
December 8, 2011, as optional in order to avoid delaying issuance of 
the AD. We have revised paragraph (g) of this AD accordingly. We are 
currently considering additional rulemaking to require the modification 
and post-modification inspections.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the 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 (76 FR 54405, September 1, 2011) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 54405, September 1, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 228 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                        Labor cost          Parts cost       Cost per product                  Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...........................  3 work-hours x $85 per             $0   $255 per inspection      $58,140 per inspection cycle.
                                        hour = $255 per                         cycle.
                                        inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------


[[Page 21428]]

    We estimate the following costs to do any necessary replacements/
modifications that would be required based on the results of the 
required inspection. We have no way of determining the number of 
aircraft that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                    Action                                    Labor cost                 Parts cost    product
----------------------------------------------------------------------------------------------------------------
Replacement of latch pins.....................  8 work-hours x $85 per hour = $680....           $0         $680
Modification of latch fittings................  36 hours x $85 per work-hours = $3,060            0        3,060
----------------------------------------------------------------------------------------------------------------

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):

2012-07-07 The Boeing Company: Amendment 39-17013; Docket No. FAA-
2011-0915; Directorate Identifier 2011-NM-020-AD.

(a) Effective Date

    This AD is effective May 15, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes; certificated 
in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53: Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of fractured latch pins found in 
service; investigation revealed that the cracking and subsequent 
fracture were initiated by fatigue and propagated by a combination 
of fatigue and stress corrosion. We are issuing this AD to detect 
and correct fractured or broken latch pins, which could result in a 
forward or aft lower lobe cargo door opening and detaching during 
flight, and consequent rapid decompression of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections

    Before the accumulation of 6,000 total flight cycles, or within 
1,000 flight cycles after the effective date of this AD, whichever 
occurs later: Do a general visual inspection for broken or missing 
latch pins of the lower sills of the forward and aft lower lobe 
cargo doors, and a detailed inspection for cracking of the latch 
pins, in accordance with paragraph 3.B., ``Work Instructions,'' of 
Boeing Alert Service Bulletin 747-53A2835, dated October 28, 2010; 
or Boeing Alert Service Bulletin 747-53A2835, Revision 1, dated 
December 8, 2011. Repeat the inspections thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2835, dated October 28, 2010; 
or Boeing Alert Service Bulletin 747-53A2835, Revision 1, dated 
December 8, 2011. Before further flight, do all applicable 
corrective actions, in accordance with paragraph 3.B., ``Work 
Instructions,'' of Boeing Alert Service Bulletin 747-53A2835, dated 
October 28, 2010; or Boeing Alert Service Bulletin 747-53A2835, 
Revision 1, dated December 8, 2011.

(h) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided the 
cabin is not pressurized.

(i) 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 the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 ODA that has been authorized by the 
Manager, Seattle

[[Page 21429]]

ACO, to make those findings. For a repair method to be approved, the 
repair must meet the certification basis of the airplane.

(j) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: (425) 917-6428; fax: (425) 917-6590; email: 
nathan.p.weigand@faa.gov.

(k) Material Incorporated by Reference

    You must use the following service information to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following 
service information.
    (1) Boeing Alert Service Bulletin 747-53A2835, dated October 28, 
2010.
    (2) Boeing Alert Service Bulletin 747-53A2835, Revision 1, dated 
December 8, 2011.
    (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; email me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com.
    (4) You may review copies of the referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, Washington. For information on the availability of this 
material at the FAA, call 425-227-1221.
    (5) You may also review copies of the 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 28, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-8232 Filed 4-9-12; 8:45 am]
BILLING CODE 4910-13-P