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75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(5) You may view this service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on June 25, 2014.

Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2014–15527 Filed 7–14–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0973; Directorate Identifier 2013–NM–139–AD; Amendment**  **39–17893; AD 2014–13–17]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of failures of the right inner tank fuel pump. This AD requires repetitive functional tests of the circuit breakers for the fuel pump power supply, and replacement of certain circuit breakers. We are issuing this AD
to detect and correct failure of the circuit breakers for the fuel pump power supply, which could result in a fuel pump overheating, leading to a fuel tank explosion.

**DATES :**  This AD becomes effective August 19, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 19, 2014. **ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0973; or in person at the 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.

For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;

Internet http://www.airbus.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.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125;
fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 series airplanes; Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on November 22, 2013 (78 FR 70003).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0163, dated July 24, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI

states:

Two successive failures have been reported of a Right Hand #1 inner tank fuel pump, Part Number 2052Cxx series (with placeholder ‘‘xx’’ indicating numerals). The fix consisted in the replacement of the pump, the
associated circuit breaker and the AC [alternating current] bus load relay.

Investigations determined that, in case of loss of one phase on the pump supply and the associated circuit breaker failing to trip, the fuel pump thermal fuses may not operate as quickly as expected. This condition, if not detected and corrected, would result in an overheat condition of the fuel pump in excess of

200 °C and could lead to a fuel tank explosion.

To address this potential unsafe condition, Airbus issued Alert Operator Transmission (AOT) A28W002–13 providing instructions
for a functional test of circuit breakers and

corrective action.

For the reasons described above, as a temporary measure until further notice, this [EASA] AD mandates functional tests of the affected fuel pump power supply circuit breakers, and, depending on findings, replacement of circuit breakers.

This [EASA] AD will be followed by further [EASA] AD action.

You may examine the MCAI in the
AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0973-

0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (78 FR 70003, November 22, 2013) or on the determination of the cost to the public.

‘‘Contacting the Manufacturer’’ Paragraph in This AD

Since late 2006, we have included a standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD.

The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved.

In the NPRM (78 FR 70003, November 22, 2013), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority design organization approval (DOA), as applicable, to refer to a DAH authorized


### 41099 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

to approve required repairs for the proposed AD.

No comments were provided to the NPRM (78 FR 70003, November 22, 2013) about these proposed changes. However, a comment was provided for another NPRM, Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013). The commenter stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an
AD mandated Airbus service bulletin.’’

This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the
manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19.

To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed that paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA DOA. Where necessary throughout this AD, we also replaced any reference to approvals of
corrective actions with a reference to the Contacting the Manufacturer paragraph.

The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and
information contained in the documentare EASA-approved, which is also FAAapproved. Messages and other information provided by the
manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information.

This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is
also consistent with the
recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in
manufacturers’ service instructions that are ‘‘Required for Compliance’’ with
ADs. We continue to work with manufacturers to implement this
recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance.

Other commenters to the NPRM discussed previously, Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013), pointed out that in many cases the foreign
manufacturer’s service bulletin and the foreign authority’s MCAI might have
been issued some time before the FAA AD. Therefore, the DOA might have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition,
before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the
manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit.

Based on these comments, weremoved the requirement that the DAHprovided repair specifically refer to this AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the
unsafe condition addressed in this AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘DAH with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH in the Contacting the Manufacturer paragraph
of this AD.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (78 FR 70003, November 22, 2013) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 70003, November 22, 2013).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Costs of Compliance

We estimate that this AD affects 156 airplanes of U.S. registry.

We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $85 per test, or $13,260 per test for U.S.-registered airplanes.

We have received no definitive data that would enable us to provide cost
estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking

action.

Regulatory Findings

We determined that 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


### 41100 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

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 the 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.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0973; 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 street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES**
section.

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.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

2014–13–17 Airbus: Amendment 39–17893. Docket No. FAA–2013–0973; Directorate
Identifier 2013–NM–139–AD.

(a) Effective Date

This AD becomes effective August 19,

2014.

(b) Affected ADs

None.

(c) Applicability

This AD applies to the Airbus airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD; certificated in any category; all serial numbers. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes.

(2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes.

(3) Model A300 B4–605R and B4–622R airplanes.

(4) Model A300 F4–605R and F4–622R airplanes.

(5) Model A300 C4–605R Variant F airplanes.

(6) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes.

(d) Subject

Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

This AD was prompted by reports of failures of the right inner tank fuel pump. We are issuing this AD to detect and correct
failure of the circuit breakers for the fuel pump power supply, which could result in a fuel pump overheating, leading to a fuel tank explosion.

(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Repetitive Functional Tests of Circuit
Breakers

(1) Within 6 months or 500 flight hours after the effective date of this AD, whichever
occurs first: Do a functional test of the circuit breakers for the fuel pump power supply, as identified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, as applicable, in accordance with Airbus Alert Operators Transmission A28W002–13, dated July 23, 2013. Repeat the functional test thereafter at intervals not to exceed 6 months or 500 flight hours, whichever occurs first.

(i) For Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes: Inner and outer pump, No. 1 and No. 2 left-hand (LH) side and right-hand (RH) side.

(ii) For Airbus Model A300 B4–2C, B4– 103, B4–203, B4–601, B4–603, B4–620, and B4–622 airplanes; and A310–203, –204, –221, and –222 airplanes:

(A) Inner and outer pump, No. 1 and No. 2, LH and RH; and

(B) Center pump, LH and RH. (iii) For Airbus Model A300 B4–605R, B4– 622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; and Model A310–304, –322, –324, and –325 airplanes:

(A) Inner and outer pump, No. 1 and No. 2, LH and RH;

(B) Center pump, LH and RH; and (C) Trim tank pump No. 1 and No. 2. (2) If, during any functional test required by paragraph (g)(1) of this AD, any circuit breaker fails any functional test, or any circuit breaker is found to be stuck closed, before further flight, replace the affected circuit breaker with a serviceable part, in accordance with Airbus Alert Operators Transmission A28W002–13, dated July 23,

2013.

(3) The replacement of one or more circuit breakers as required by paragraph (g)(2) of this AD does not terminate the repetitive functional tests required by paragraph (g)(1)
of this AD.

(h) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(i) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0163, dated July 24, 2013, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov/#!document Detail;D=FAA-2013-0973-0002.

(j) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(i) Airbus Alert Operators Transmission A28W002–13, dated July 23, 2013.

(ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.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.


### 41101 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on June 25,

2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–15800 Filed 7–14–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0867; Directorate Identifier 2013–NM–115–AD; Amendment**  **39–17853; AD 2014–11–03]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This AD was prompted by reports of severe corrosion on bonding jumpers installed on the flight control surfaces. This AD requires repetitive bonding jumper inspections for corrosion, sealant disbond, and insufficient sealant coverage; and corrective actions if necessary. This AD also specifies an optional inspection for corrosion damage of the bonding brackets, and corrective actions if necessary, which would terminate the repetitive inspections. For certain airplanes, this AD requires installing certain bonding jumpers, and replacing single-tabbed brackets with two-tabbed brackets. We are issuing this AD to detect and correct corrosion on bonding jumpers installed on the flight control surfaces, which, in the event of a lightning strike, could damage the actuator control electronics (ACEs) and result in the loss of the ability to command individual flight control
surfaces or cause uncommanded motion of individual flight control surfaces. **DATES :**  This AD is effective August 19,

2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 19, 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 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

You may examine the AD docket on
the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0867; 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 :**  Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6482; fax: 425–917–6590; email: Georgios.Roussos@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 777–200, –200LR, –300, and –300ER series airplanes. The NPRM published in the Federal Register on October 25, 2013 (78 FR 63903). The NPRM was prompted by reports of severe corrosion on bonding jumpers installed on the flight control surfaces. The NPRM proposed to require repetitive bonding jumper inspections for corrosion, sealant disbond, and insufficient sealant coverage; and corrective actions if necessary. The NPRM also specified an optional inspection for corrosion damage of the bonding brackets, and corrective actions if necessary, which would terminate the repetitive inspections. For certain airplanes, the NPRM proposed installing certain bonding jumpers, and replacing single-tabbed brackets with two-tabbed brackets. We are issuing this AD to detect and correct corrosion on bonding jumpers installed on the flight control surfaces, which, in the event of a lightning strike, could damage the ACEs and result in the loss of the ability to command individual flight control
surfaces or cause uncommanded motion of individual flight control surfaces.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 63903, October 25, 2013) and the FAA’s response to each comment.

Request To Base Compliance Time on

AD Issue Date

American Airlines (AAL) requested that paragraph (f) of the proposed AD (78 FR 63903, October 25, 2013) be revised to allow operators to comply with Boeing Service Bulletin 777– 27A0078, Revision 1, dated April 1, 2013, within 36 months after the AD effective date. AAL stated that Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, was issued with a compliance time of 36 months from the original release of the service bulletin. AAL explained that after Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009, was released, Boeing accomplished a
service bulletin validation on another operator’s airplane and found many discrepancies and errors with the work instructions and parts required, resulting in Revision 1 of Boeing Service Bulletin 777–27A0078, dated April 1,
2013. AAL stated that due to the issues still existing in the work instructions for Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009, and a long lead time on the part kits, operators will be unable to accomplish Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013, by the compliance time given without severe disruption of schedules.

We agree with the commenter’s request. We agree that the compliance
time should be based on the effective
date of this final rule and not on the original issue date of Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013. We had already
included this information in the proposed AD (78 FR 63903, October 25, 2013), paragraph (j)(1) of this AD, as