Source: https://www.federalregister.gov/documents/2015/01/22/2015-00009/airworthiness-directives-the-boeing-company-airplanes
Timestamp: 2018-04-24 01:30:19
Document Index: 679996143

Matched Legal Cases: ['art 39', '§\u200939', 'art 1', 'art 2', 'art 3', 'art 4', 'art 4', 'art 4', 'art 4', 'art 5', 'art 6']

This AD is effective February 26, 2015.
80 FR 3158
3158-3161 (4 pages)
Docket No. FAA-2014-0580
Directorate Identifier 2014-NM-081-AD
Amendment 39-18062
AD 2015-01-01
2015-00009
FAA-2014-0580
2014-NM-081-AD The Boeing Company Model 777-200 and -300 series airplanes
(g) Retained Inspections and Corrective Actions With Revised Service Information
(h) Retained Corrective Action With Revised Service Information
(i) Retained Optional Terminating Action With Revised Service Information
https://www.federalregister.gov/d/2015-00009 https://www.federalregister.gov/d/2015-00009
We are superseding Airworthiness Directive (AD) 2011-09-11, for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2011-09-11 required repetitive inspections for hydraulic fluid contamination of the interior of the strut disconnect assembly; repetitive inspections for discrepancies of the interior of the strut disconnect assembly, if necessary; repetitive inspections of the exterior of the strut disconnect assembly for cracks, if necessary; corrective action if necessary; and an optional terminating action for the inspections. This new AD adds, for certain airplanes, an inspection of the side and top cover plates to determine if all cover plate attach fasteners have been installed, and installing any missing fasteners including doing an inspection for damage, and repair if necessary. This AD was prompted by reports of side and top cover plates installed with missing fastener bolts, which results in an unsealed opening on the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly; and also to detect and correct missing fasteners, which results in unsealed openings on the system disconnect assembly. Both unsafe conditions can compromise the engine firewall and result in fire hazards for both the engine compartment and the strut.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 26, 2015.
The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 6, 2011 (76 FR 24354, May 2, 2011).
For service information identified in this AD, contact Boeing Start Printed Page 3159Commercial 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.
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0580; 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.
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011). AD 2011-09-11 applied to The Boeing Company Model 777-200 and - 300 series airplanes equipped with Pratt and Whitney engines. The NPRM published in the Federal Register on August 26, 2014 (79 FR 50877).
We gave the public the opportunity to participate in developing this AD. We have considered the comments received. United Airlines and Boeing supported the NPRM (79 FR 50877, August 26, 2014).
Are consistent with the intent that was proposed in the NPRM (79 FR 50877, August 26, 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 50877, August 26, 2014).
We estimate that this AD affects 54 airplanes of U.S. registry.
Inspections [retained actions from AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011)] 18 work-hours × $85 per hour = $1,530 $0 $1,530 $82,620
Inspection of cover plate fasteners [new action] 8 work-hours × $85 per hour = $680 0 680 36,720
We estimate the following costs to do any necessary repairs/replacements that will be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs/replacements:
Replacement [retained actions from AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011)] 35 work-hours × $85 per hour = $2,975 $420,440 $423,415
Inspection of electrical components and installation of new fasteners [new actions] 14 work-hours × $85 per hour = $1,190 458 1,648
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 Start Printed Page 3160is 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.
2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011-09-11, Amendment 39-16673 ( 76 FR 24354, May 2, 2011), and adding the following new AD:
2015-01-01 The Boeing Company: Amendment 39-18062; Docket No. FAA-2014-0580; Directorate Identifier 2014-NM-081-AD.
This AD replaces AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011).
This AD applies to The Boeing Company Model 777-200 and -300 series airplanes, certificated in any category; equipped with Pratt and Whitney engines; as identified in Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014.
This AD was prompted by reports of side and top cover plates installed with missing fastener bolts, which results in an unsealed opening on the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly; and also to detect and correct missing fasteners, which results in unsealed openings on the system disconnect assembly. Both unsafe conditions can compromise the engine firewall and result in fire hazards for both the engine compartment and the strut.
This paragraph restates the requirements of paragraph (g) of AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with revised service information. Within 12 months after June 6, 2011 (the effective date of AD 2011-09-11): Do a general visual inspection for hydraulic fluid contamination of the interior of the strut disconnect assembly, in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
(2) For airplanes on which hydraulic fluid contamination is found (Condition 2): Before further flight, do a detailed inspection for discrepancies (e.g., hydraulic fluid coking, heat discoloration, cracks, and etching or pitting) of the interior of the strut disconnect assembly, in accordance with Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
(A) Within 300 flight cycles after doing the inspection required by paragraph (g)(2) of this AD: Do a detailed inspection of the exterior of the strut disconnect assembly for cracks, in accordance with Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014; and repeat the detailed inspection thereafter at intervals not to exceed 300 flight cycles. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
(B) Within 6,000 flight cycles or 750 days after hydraulic fluid coking and/or heat discoloration was found during the inspection required by paragraph (g)(2) of this AD, whichever occurs first: Replace the titanium system disconnect assembly with an Inconel system, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
This paragraph restates the requirements of paragraph (h) of AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with revised service information. For airplanes on which any crack, etching, or pitting is found during any inspection required by paragraph (g)(2) or (g)(2)(ii)(A) of this AD (Condition 3): Before further flight, replace the titanium system disconnect assembly with an Inconel system, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
This paragraph restates the requirements of paragraph (i) of AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with revised service information. Replacing the titanium system disconnect assembly with an Inconel system disconnect assembly in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 2014; terminates the actions required by paragraphs (g) and (h) of this AD. As of the effective date of this AD, use only Boeing Service Bulletin 777-54A0024, Start Printed Page 3161Revision 2, dated January 23, 2014, for accomplishing the actions in this paragraph.
For airplanes on which the system disconnect assembly has been replaced in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, dated April 1, 2010; or Revision 1, dated November 4, 2010: Within 1,125 days after the effective date of this AD, do a detailed inspection of the cover plate fasteners to determine if all cover plate attach fasteners are installed, in accordance with Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014. If any fastener is missing, before further flight, install fasteners (including doing a detailed inspection for damage of the electrical components and repairing any damaged components), in accordance with Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014.
This paragraph restates the credit provided by paragraph (j) of AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011). This paragraph provides credit for the corresponding actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before June 6, 2011 (the effective date of AD 2011-09-11) using Boeing Service Bulletin 777-54A0024, dated April 1, 2010, which is not incorporated by reference in this AD.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD.
(3) The following service information was approved for IBR on February 26, 2015.
(i) Boeing Service Bulletin 777-54A0024, Revision 2, dated January 23, 2014.
(4) The following service information was approved for IBR on June 6, 2011 (76 FR 24354, May 2, 2011).
(i) Boeing Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010.
Issued in Renton, Washington, on December 22, 2014.
[FR Doc. 2015-00009 Filed 1-21-15; 8:45 am]