Airworthiness Directives; The Boeing Company Airplanes, 30005-30008 [2014-12093]

Download as PDF 30005 Rules and Regulations Federal Register Vol. 79, No. 101 Tuesday, May 27, 2014 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. FARM CREDIT ADMINISTRATION 12 CFR Part 620 Disclosure to Shareholders CFR Correction In Title 12 of the Code of Federal Regulations, Parts 600 to 899, revised as of January 1, 2014, on page 242, in § 620.2, paragraph (e) is reinstated to read as follows: § 620.2 Preparing and filing reports. * * * * * (e) All items of essentially the same character as items required to be reported in the reports of condition and performance pursuant to part 621 of this chapter shall be prepared in accordance with the rules set forth in part 621. * * * * * [FR Doc. 2014–12307 Filed 5–23–14; 8:45 am] BILLING CODE 1505–01–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0618; Directorate Identifier 2007–NM–355–AD; Amendment 39–17844; AD 2014–09–09] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. emcdonald on DSK67QTVN1PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes. This AD was prompted by reports of two in-service occurrences on Model 737–400 airplanes of total loss of SUMMARY: VerDate Mar<15>2010 17:52 May 23, 2014 Jkt 232001 boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and in-flight shutdown of the engine. This AD requires revising the maintenance program to incorporate a revision to the Airworthiness Limitations Section of the maintenance planning data (MPD) document. We are issuing this AD to detect and correct failure of the engine fuel suction feed of the fuel system, which, in the event of total loss of the fuel boost pumps, could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane. DATES: This AD is effective July 1, 2014. 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 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2008– 0618; 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: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6438; fax: 425–917– 6590; email: suzanne.lucier@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a second supplemental notice of proposed rulemaking (SNPRM) PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes. The second SNPRM published in the Federal Register on July 30, 2013 (78 FR 45898). The second SNPRM proposed to add Model 777F series airplanes to the applicability. We preceded the second SNPRM with the first SNPRM, which published in the Federal Register on March 7, 2013 (78 FR 14722). The first SNPRM proposed to revise the maintenance program to incorporate a revision to the Airworthiness Limitations Section of the maintenance planning data (MPD) document. We preceded the first SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on June 6, 2008 (73 FR 32253). The NPRM was prompted by reports of two in-service occurrences on Model 737– 400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and inflight shutdown of the engine. The subject area on Model 777 airplanes is almost identical to that area on Model 737–400 airplanes; therefore, Model 777 airplanes may be subject to the unsafe condition revealed on Model 737–400 airplanes. The NPRM proposed to require performing repetitive operational tests of the engine fuel suction feed of the fuel system, and other related testing if necessary. We are issuing this AD to detect and correct failure of the engine fuel suction feed of the fuel system, which, in the event of total loss of the fuel boost pumps, could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the second SNPRM (78 FR 45898, July 30, 2013) and the FAA’s response to each comment. FedEx concurs with the proposed requirements. Request To Allow the Use of Later Revisions of the Maintenance Planning Document (MPD) United Airlines (UAL) asked that we allow using the latest MPD revision of E:\FR\FM\27MYR1.SGM 27MYR1 30006 Federal Register / Vol. 79, No. 101 / Tuesday, May 27, 2014 / Rules and Regulations May 2013 for accomplishing the required actions. UAL stated that paragraph (l) of the second SNPRM (78 FR 45898, July 30, 2013) provides credit for doing the actions required by paragraph (g) of the second SNPRM before the effective date of the AD, if the actions were done using Revision February 2012 of the MPD. UAL suggested that credit for Revision May 2013 of the MPD also be included in paragraph (l) of the second SNPRM. We agree to give credit for the latest revision of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001–9, which is Revision dated June 2013; provided the revised ‘‘interval’’ specified in Appendix 1 of this AD is incorporated into the existing maintenance program within 90 days after the effective date of this AD. We have revised paragraph (i) of this AD accordingly. necessary. We have made no change to the final rule in this regard. Request To Clarify Reason for the Unsafe Condition Boeing asked that we clarify the reason for the unsafe condition identified in the second SNPRM (78 FR 45898, July 30, 2013). Boeing asked that we provide additional clarification that there are no reports of any in-service events on Model 777 airplanes. We acknowledge the commenter’s concern, but do not find it necessary to clarify the unsafe condition further. We clarified the reason for the unsafe condition in the first SNPRM (78 FR 45898, July 30, 2013) per a similar request from Boeing regarding the fact that there had been no events on Model 777 airplanes. In light of this, we find that further clarification is not Change to Final Rule We removed the on-condition costs specified in the ‘‘Costs of Compliance’’ section of this final rule because there are no on-condition actions. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD affects 676 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Cost per product Maintenance Program Revision ........................... 1 work-hour × $85 per hour = $85 ...................... $85 per test ........... 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. emcdonald on DSK67QTVN1PROD with RULES 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: VerDate Mar<15>2010 17:52 May 23, 2014 Jkt 232001 (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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Cost on U.S. operators $57,460, per test. FAA–2008–0618; Directorate Identifier 2007–NM–355–AD. (a) Effective Date This AD is effective July 1, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 2800, Aircraft Fuel System. (e) Unsafe Condition This AD was prompted by reports of two in-service occurrences on Model 737–400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and in-flight shutdown of the engine. We are issuing this AD to detect and correct failure of the engine fuel suction feed of the fuel system, which, in the event of total loss of the fuel boost pumps, could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane. ■ (f) Compliance Comply with this AD within the compliance times specified, unless already done. 2014–09–09 The Boeing Company: Amendment 39–17844; Docket No. (g) Maintenance Program Revision Within 90 days after the effective date of this AD: Revise the maintenance program to incorporate the airworthiness limitation § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 79, No. 101 / Tuesday, May 27, 2014 / Rules and Regulations (AWL) identified in Appendix 1 of this AD, AWL No. 28–AWL–101, Engine Fuel Suction Feed Operational Test. The initial compliance time for accomplishing AWL No. 28–AWL–101 is within 7,500 flight hours or 3 years after the effective date of this AD, whichever is first. (h) No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs) After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., tests), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j) of this AD. (i) Credit for Actions Accomplished in Accordance With Previous Service Information This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using AWL No. 28– AWL–101, Engine Fuel Suction Feed AWL No. Task 28–AWL–101 .... ALI ............... Operational Test, of Section D.2., Engine Suction Fuel System, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D622W001–9, Revision February 2012, or Revision June 2013, of the Boeing 777 Maintenance Planning Data (MPD) Document, provided the revised ‘‘interval’’ specified in Appendix 1 of this AD is incorporated into the existing maintenance program within 90 days after the effective date of this AD. (j) 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. Interval (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. (k) Related Information (1) For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: 425–917–6438; fax: 425–917– 6590; email: suzanne.lucier@faa.gov. (2) For service information identified in this AD that is not incorporated by reference, 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. (l) Material Incorporated by Reference None. Appendix 1 of AD 2014–09–09 Applicability 7,500 FH or 3 years, whichever is first. ALL .............. 30007 Description Engine Fuel Suction Feed Operational Test. emcdonald on DSK67QTVN1PROD with RULES An Engine Fuel Suction Feed Operational Test must be accomplished successfully on each engine individually. This test is required in order to protect against engine flameout during suction feed operations, and must meet the following requirements (refer to Boeing AMM 28–22–00): Fuel Tank Quantity Limitations: Engine No. 1 a. The Center Tank Fuel Quantity must not exceed 5,000 lbs (2,270 kg). b. The Main Tank No. 1 Fuel Quantity must be between 1,400 lbs–1,600 lbs (600 kg–800 kg). NOTE: Excess fuel can be transferred to Main Tank No. 2. Engine No. 2 a. The Center Tank Fuel Quantity must not exceed 5,000 lbs (2,270 kg). b. The Main Tank No. 2 Fuel Quantity must be between 1,400 lbs–1,600 lbs (600 kg–800 kg). NOTE: Excess fuel can be transferred to Main Tank No. 1. Test Procedural Limitations: 1. The Fuel Cross-Feed Valve must be CLOSED. 2. The APU Selector Switch must be OFF. 3. Idle Engine Warm-up time of minimum two minutes with Boost Pump ON. 4. Idle Engine Suction Feed (Boost Pump OFF) operation for a minimum of five minutes. NOTE: APU may be used to start the engines provided the Fuel Tank Quantity and Test Procedural Limitations are met. The test is considered a success if engine operation is maintained during the five-minute period and engine parameters (N1, N2, and Fuel Flow) do not decay relative to those observed with Boost Pump ON. A suction feed system that fails the operational test must be repaired or maintained, and successfully pass the Engine Suction Feed Operational Test prior to further flight. VerDate Mar<15>2010 17:52 May 23, 2014 Jkt 232001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1 30008 Federal Register / Vol. 79, No. 101 / Tuesday, May 27, 2014 / Rules and Regulations Issued in Renton, Washington, on April 18, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–12093 Filed 5–23–14; 8:45 am] BILLING CODE 4910–13–P 468444; Internet https:// www.bombardier.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. Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2012– 1103; 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. [Docket No. FAA–2012–1103; Directorate Identifier 2012–NM–131–AD; Amendment 39–17842; AD 2014–09–07] 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 certain The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes. This AD was prompted by reports of cracking of the forward bulkhead web, web stiffeners, attachment angles, and thermal anti-ice (TAI) spray ring assemblies of the engine air intake cowl. This AD requires replacing the forward bulkhead assembly, TAI spray ring assembly, and attachment fittings of the air intake cowl. We are issuing this AD to prevent the failure of air intake cowl components due to cracking, which could result in the air intake cowl separating from the engine and striking critical airplane control surfaces that could result in a loss of airplane control; severe engine damage and loss of thrust; or large parts striking a person or property on the ground. DATES: This AD is effective July 1, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 1, 2014. ADDRESSES: For Rolls-Royce service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 011 44 1332 242424; fax 011 44 1332 249936; email https://www.rollsroyce.com/contact/civil_team.jsp; Internet https://www.aeromanager.com. For Bombardier service information identified in this AD, contact Short Brothers PLC, Airworthiness, P.O. Box 241, Airport Road, Belfast, BT3 9DZ Northern Ireland; telephone +44(0)2890–462469; fax +44(0)2890– emcdonald on DSK67QTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:52 May 23, 2014 Jkt 232001 FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917– 6501; fax: (425) 917–6590; email: kevin.nguyen@faa.gov. 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 certain The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes. The NPRM published in the Federal Register on October 19, 2012 (77 FR 64242). The NPRM was prompted by reports of cracking of the forward bulkhead web, web stiffeners, attachment angles, and thermal anti-ice (TAI) spray ring assemblies of the engine air intake cowl. The NPRM proposed to require replacing the forward bulkhead assembly, TAI spray ring assembly, and attachment fittings of the air intake cowl. We are issuing this AD to prevent the failure of air intake cowl components due to cracking, which could result in the air intake cowl separating from the engine and striking critical airplane control surfaces that could result in a loss of airplane control; severe engine damage and loss of thrust; or large parts striking a person or property on the ground. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 64242, October 19, 2012) and the FAA’s response to each comment. Requests To Delay Final Rule Pending Modification as Terminating Action DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 Comments FedEx, American Airlines (AAL), and United Airlines (UAL) requested that we delay issuance of this final rule until the manufacturer can release service information that contains instructions for a modification as terminating action for the repetitive replacements proposed in the NPRM (77 FR 69242, October 19, 2012). In lieu of that, FedEx and AAL requested we include a modification as terminating action. FedEx and AAL stated that it would be more beneficial to accomplish the terminating modification rather than doing the interim replacements of the air intake cowl bulkhead assemblies or parts. UAL noted that airlines are working with Boeing to obtain improvements to the current design, which includes a threepart solution to most structural design deficiencies. FedEx explained that Rolls-Royce was scheduled to release service information including a terminating modification for the repetitive replacements during the first quarter of 2013. UAL stated repetitive replacement of the forward bulkhead is expensive and does not solve the inherent design problem. We partially agree. We agree that a terminating modification, if available, should be included as part of this final rule, because eliminating the in-service safety issue is a preferred choice over repetitive replacement of assemblies or parts. However, we disagree with delaying issuance of this final rule until service information containing procedures for a terminating modification becomes available. We have not received an exact date for release of the planned RollsRoyce service information. We have determined that to delay this final rule would be inappropriate, since we have determined that such a delay would not adequately address the unsafe condition in a timely manner and that replacing the forward bulkhead assembly components must be done to ensure continued safety. When the terminating modification becomes available, we might consider additional rulemaking. Operators may apply for approval of an alternative method of compliance (AMOC) for these actions in accordance with the provisions of paragraph (l) of E:\FR\FM\27MYR1.SGM 27MYR1

Agencies

[Federal Register Volume 79, Number 101 (Tuesday, May 27, 2014)]
[Rules and Regulations]
[Pages 30005-30008]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-12093]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0618; Directorate Identifier 2007-NM-355-AD;
Amendment 39-17844; AD 2014-09-09]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series
airplanes. This AD was prompted by reports of two in-service
occurrences on Model 737-400 airplanes of total loss of boost pump
pressure of the fuel feed system, followed by loss of fuel system
suction feed capability on one engine, and in-flight shutdown of the
engine. This AD requires revising the maintenance program to
incorporate a revision to the Airworthiness Limitations Section of the
maintenance planning data (MPD) document. We are issuing this AD to
detect and correct failure of the engine fuel suction feed of the fuel
system, which, in the event of total loss of the fuel boost pumps,
could result in dual engine flameout, inability to restart the engines,
and consequent forced landing of the airplane.

DATES: This AD is effective July 1, 2014.

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 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2008-
0618; 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: Sue Lucier, Aerospace Engineer,
Propulsion Branch, ANM-140S, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6438; fax: 425-917-6590; email:
suzanne.lucier@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a second supplemental notice of proposed rulemaking
(SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all
The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series
airplanes. The second SNPRM published in the Federal Register on July
30, 2013 (78 FR 45898). The second SNPRM proposed to add Model 777F
series airplanes to the applicability.
We preceded the second SNPRM with the first SNPRM, which published
in the Federal Register on March 7, 2013 (78 FR 14722). The first SNPRM
proposed to revise the maintenance program to incorporate a revision to
the Airworthiness Limitations Section of the maintenance planning data
(MPD) document.
We preceded the first SNPRM with a notice of proposed rulemaking
(NPRM) that published in the Federal Register on June 6, 2008 (73 FR
32253). The NPRM was prompted by reports of two in-service occurrences
on Model 737-400 airplanes of total loss of boost pump pressure of the
fuel feed system, followed by loss of fuel system suction feed
capability on one engine, and in-flight shutdown of the engine. The
subject area on Model 777 airplanes is almost identical to that area on
Model 737-400 airplanes; therefore, Model 777 airplanes may be subject
to the unsafe condition revealed on Model 737-400 airplanes. The NPRM
proposed to require performing repetitive operational tests of the
engine fuel suction feed of the fuel system, and other related testing
if necessary.
We are issuing this AD to detect and correct failure of the engine
fuel suction feed of the fuel system, which, in the event of total loss
of the fuel boost pumps, could result in dual engine flameout,
inability to restart the engines, and consequent forced landing of the
airplane.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the second
SNPRM (78 FR 45898, July 30, 2013) and the FAA's response to each
comment. FedEx concurs with the proposed requirements.

Request To Allow the Use of Later Revisions of the Maintenance Planning
Document (MPD)

United Airlines (UAL) asked that we allow using the latest MPD
revision of

[[Page 30006]]

May 2013 for accomplishing the required actions. UAL stated that
paragraph (l) of the second SNPRM (78 FR 45898, July 30, 2013) provides
credit for doing the actions required by paragraph (g) of the second
SNPRM before the effective date of the AD, if the actions were done
using Revision February 2012 of the MPD. UAL suggested that credit for
Revision May 2013 of the MPD also be included in paragraph (l) of the
second SNPRM.
We agree to give credit for the latest revision of Section 9,
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), D622W001-9, which is Revision dated June 2013;
provided the revised ``interval'' specified in Appendix 1 of this AD is
incorporated into the existing maintenance program within 90 days after
the effective date of this AD. We have revised paragraph (i) of this AD
accordingly.

Request To Clarify Reason for the Unsafe Condition

Boeing asked that we clarify the reason for the unsafe condition
identified in the second SNPRM (78 FR 45898, July 30, 2013). Boeing
asked that we provide additional clarification that there are no
reports of any in-service events on Model 777 airplanes.
We acknowledge the commenter's concern, but do not find it
necessary to clarify the unsafe condition further. We clarified the
reason for the unsafe condition in the first SNPRM (78 FR 45898, July
30, 2013) per a similar request from Boeing regarding the fact that
there had been no events on Model 777 airplanes. In light of this, we
find that further clarification is not necessary. We have made no
change to the final rule in this regard.

Change to Final Rule

We removed the on-condition costs specified in the ``Costs of
Compliance'' section of this final rule because there are no on-
condition actions.

Conclusion

We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed.

Costs of Compliance

We estimate that this AD affects 676 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Maintenance Program Revision.... 1 work-hour x $85 $85 per test................ $57,460, per test.
per hour = $85.
----------------------------------------------------------------------------------------------------------------

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):

2014-09-09 The Boeing Company: Amendment 39-17844; Docket No. FAA-
2008-0618; Directorate Identifier 2007-NM-355-AD.

(a) Effective Date

This AD is effective July 1, 2014.

(b) Affected ADs

None.

This AD applies to all The Boeing Company Model 777-200, -200LR,
-300, -300ER, and 777F series airplanes, certificated in any
category.

(d) Subject

Air Transport Association (ATA) of America Code 2800, Aircraft
Fuel System.

(e) Unsafe Condition

This AD was prompted by reports of two in-service occurrences on
Model 737-400 airplanes of total loss of boost pump pressure of the
fuel feed system, followed by loss of fuel system suction feed
capability on one engine, and in-flight shutdown of the engine. We
are issuing this AD to detect and correct failure of the engine fuel
suction feed of the fuel system, which, in the event of total loss
of the fuel boost pumps, could result in dual engine flameout,
inability to restart the engines, and consequent forced landing of
the airplane.

(f) Compliance

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

(g) Maintenance Program Revision

Within 90 days after the effective date of this AD: Revise the
maintenance program to incorporate the airworthiness limitation

[[Page 30007]]

(AWL) identified in Appendix 1 of this AD, AWL No. 28-AWL-101,
Engine Fuel Suction Feed Operational Test. The initial compliance
time for accomplishing AWL No. 28-AWL-101 is within 7,500 flight
hours or 3 years after the effective date of this AD, whichever is
first.

(h) No Alternative Actions, Intervals, and/or Critical Design
Configuration Control Limitations (CDCCLs)

After accomplishing the revision required by paragraph (g) of
this AD, no alternative actions (e.g., tests), intervals, or CDCCLs
may be used unless the actions, intervals, or CDCCLs are approved as
an alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (j) of this AD.

(i) Credit for Actions Accomplished in Accordance With Previous Service
Information

This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using AWL No. 28-AWL-101, Engine Fuel
Suction Feed Operational Test, of Section D.2., Engine Suction Fuel
System, of Section 9, Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), D622W001-9, Revision
February 2012, or Revision June 2013, of the Boeing 777 Maintenance
Planning Data (MPD) Document, provided the revised ``interval''
specified in Appendix 1 of this AD is incorporated into the existing
maintenance program within 90 days after the effective date of this
AD.

(j) 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.

(k) Related Information

(1) For more information about this AD, contact Sue Lucier,
Aerospace Engineer, Propulsion Branch, ANM-140S, 1601 Lind Avenue
SW., Renton, Washington 98057-3356; phone: 425-917-6438; fax: 425-
917-6590; email: suzanne.lucier@faa.gov.
(2) For service information identified in this AD that is not
incorporated by reference, 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.

(l) Material Incorporated by Reference

None.

Appendix 1 of AD 2014-09-09

--------------------------------------------------------------------------------------------------------------------------------------------------------
AWL No. Task Interval Applicability Description
--------------------------------------------------------------------------------------------------------------------------------------------------------
28-AWL-101....................... ALI.................. 7,500 FH or 3 years, ALL.................. Engine Fuel Suction Feed Operational Test.
whichever is first.
An Engine Fuel Suction Feed Operational Test
must be accomplished successfully on each
engine individually. This test is required
in order to protect against engine flameout
during suction feed operations, and must
meet the following requirements (refer to
Boeing AMM 28-22-00):
Fuel Tank Quantity Limitations:
Engine No. 1
a. The Center Tank Fuel Quantity must not
exceed 5,000 lbs (2,270 kg).
b. The Main Tank No. 1 Fuel Quantity must be
between 1,400 lbs-1,600 lbs (600 kg-800
kg).
NOTE: Excess fuel can be transferred to Main
Tank No. 2.
Engine No. 2
a. The Center Tank Fuel Quantity must not
exceed 5,000 lbs (2,270 kg).
b. The Main Tank No. 2 Fuel Quantity must be
between 1,400 lbs-1,600 lbs (600 kg-800
kg).
NOTE: Excess fuel can be transferred to Main
Tank No. 1.
Test Procedural Limitations:
1. The Fuel Cross-Feed Valve must be CLOSED.
2. The APU Selector Switch must be OFF.
3. Idle Engine Warm-up time of minimum two
minutes with Boost Pump ON.
4. Idle Engine Suction Feed (Boost Pump OFF)
operation for a minimum of five minutes.
NOTE: APU may be used to start the engines
provided the Fuel Tank Quantity and Test
Procedural Limitations are met.
The test is considered a success if engine
operation is maintained during the five-
minute period and engine parameters (N1,
N2, and Fuel Flow) do not decay relative to
those observed with Boost Pump ON.
A suction feed system that fails the
operational test must be repaired or
maintained, and successfully pass the
Engine Suction Feed Operational Test prior
to further flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------

[[Page 30008]]

Issued in Renton, Washington, on April 18, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-12093 Filed 5-23-14; 8:45 am]
BILLING CODE 4910-13-P

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