## 23893 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations

or policies unless they present an
irreconcilable conflict with this rule. There are no administrative procedures which must be exhausted prior to any judicial challenge to the provisions of
this direct final rule.

Paperwork Reduction Act

This rule does not contain new or
amended information collection requirements subject to the Paperwork Reduction Act of 1995 (44 U.S.C. 3501 et seq. ). It does not involve collection of new or additional information by the federal government.

E-Government Act Compliance

GIPSA is committed to complying with the E-Government Act, to promote
the use of the Internet and other information technologies to provide increased opportunities for citizen
access to Government information and services, and for other purposes.

List of Subjects in 7 CFR Part 201

Swine, Hogs, Incorporation by reference, Livestock, Measurement
standards.

For reasons set forth in the preamble, 9 CFR part 201 is amended as follows:

**PART 201—REGULATIONS UNDER**
**THE PACKERS AND STOCKYARDS**
**ACT**

■ 

### 1. The authority citation for part 201
continues to read as follows:

Authority: 7 U.S.C. 181–229c.

■ 

### 2. In § 201.71, paragraph (a) is revised
to read as follows:

**§ 201.71 Scales; accurate weights, repairs, adjustments or replacements after**  **inspection.**



### (a) All scales used by stockyard owners, swine contractors, market agencies, dealers, packers, and live poultry dealers to weigh livestock, livestock carcasses, live poultry, or feed for the purpose of purchase, sale acquisition, payment, or settlement shall be installed, maintained, and operated to ensure accurate weights. Such scales shall meet applicable requirements contained in section 5.59, Electronic Livestock, Meat, and Poultry Evaluation Systems and/or Devices, pages 5–85 and 5–86 of the ‘‘U.S. Department of Commerce, National Institute of Standards and Technology, Specifications, Tolerances, and other Technical Requirements for Weighing and Measuring Devices (NIST Handbook 44), 2013 edition’’ which is hereby incorporated by reference. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. These materials are incorporated as they exist on the date of approval and a notice of any change in these materials will be published in the Federal Register . All approved material is available for inspection at USDA, GIPSA, P&SP, 1400 Independence Ave. SW., Washington, DC 20250, 202–720–7363 and is for sale by the National Conference of Weights and Measures (NCWM), 1135 M Street, Suite 110, Lincoln, Nebraska, 68508. Information on this material may be obtained from NCWM by calling 402– 434–4880, by emailing nfo@ncwm.net,
or on the Internet at http:// www.nist.gov/owm. It is also available for inspection at the National Archives and Records Administration (NARA). For more information on the availability of this material at NARA, call 202–741– 6030 or go to http://www.archives.gov/ federal

_register/code

_of

_ federal

_ regulations/ibr

_locations.html.

* * * * *

Larry Mitchell, Administrator, Grain Inspection, Packers and Stockyards Administration.

[FR Doc. 2014–09655 Filed 4–28–14; 8:45 am]

**BILLING CODE 3410–KD–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0425; Directorate Identifier 2012–NM–224–AD; Amendment**  **39–17815; AD 2014–07–01]**

**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 747 airplanes. This AD was prompted by reports of cracking in particular areas of the bulkhead structure at body station (BS) 2598. This AD requires repetitive inspections, including post-repair and post-modification inspections, for cracking in the bulkhead structure at BS 2598; certain one-time inspections of certain fasteners and support frame modifications on certain airplanes; related investigative and corrective actions, if necessary; and an interim
modification that would terminate certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity
of the bulkhead and the horizontal stabilizer support structure, and result in loss of controllability of the airplane.

**DATES** 

### : This AD is effective June 3, 2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 3, 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– 0425; 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** 

### : Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747 airplanes. The SNPRM published in the Federal Register on January 2, 2014 (79 FR 65). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on May 28, 2013 (78 FR 31867).


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The NPRM proposed to require repetitive inspections for cracking in the bulkhead splice fitting, frame supports, forward and aft inner chords, and floor support; an inspection for cracking in the bulkhead upper web, doubler, and bulkhead lower web, and correctiveactions if necessary; and repetitive postrepair inspections of the support frame, and corrective actions, if necessary. For certain airplanes, the NPRM proposed to require:

• Inspections for cracking in the repaired area of the bulkhead, and corrective actions if necessary;

• A support frame modification and inspections, and related investigative and corrective actions, if necessary;

• Repetitive post-repair inspections of the support frame and inspections for cracking in the hinge support, and related investigative and corrective actions if necessary;

• A one-time inspection of the frame web and upper shear deck (floor support) chord aft side for fasteners; and a one-time inspection of the upper forward inner chord, frame support fitting, and splice fitting for the installation of certain fasteners; and related investigative and corrective actions if necessary; • A one-time inspection of the upper forward inner chord, frame support fitting, and splice fitting for theinstallation of certain fasteners; a onetime inspection for any repair installed on the left and right side of the aft inner chord; and related investigative and corrective actions, if necessary; and

• A one-time inspection of the support frame outer chord for cracking, and repair if necessary.

The NPRM was prompted by reports of cracking in the forward and aft inner
chord of the BS 2598 bulkhead near the upper corners of the cutout for the horizontal stabilizer rear spar, and cracking in the bulkhead upper and lower web panels near the inner chord
to shear deck connection.

The SNPRM proposed to add an optional terminating action for certain inspections and expand the inspection area for certain surface and open-hole high frequency eddy current (HFEC) inspections. We are issuing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity of the bulkhead and the horizontal stabilizer support structure, and result in loss of controllability of the airplane. Comments

We gave the public the opportunity to participate in developing this AD. We
have considered the comment received. Boeing supported the SNPRM (79 FR 65, January 2, 2014).

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the SNPRM (79 FR 65, January 2, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the SNPRM (79 FR 65, January 2, 2014).

Costs of Compliance

We estimate that this AD affects 184 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

Action Labor cost Parts
cost Cost per product Cost on U.S. operators

Bulkhead (support frame) inspection .......... 49 work-hours × $85 per hour = $4,165 per inspection cycle. $0 $4,165 per inspection cycle. $766,360 per inspection cycle. Support frame modification ......................... 315 work-hours × $85 per hour = $26,775 0 26,775 ...................... Up to $4,926,600.Support frame upper corner fastener inspection. 16 work-hours × $85 per hour = $1,360 ... 0 1,360 ........................ Up to $250,240.

Support frame post-modification/post repair

inspection. 200 work hours × $85 per hour = $17,000 0 17,000 ...................... 3,128,000.



### We estimate the following costs to do any necessary interim modification that would be required based on the results of inspection of the bulkhead specified in paragraph (g) of this AD. We have no way of determining the number of aircraft that might need this interim
modification:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Interim modification ...................................................... 4 work-hours × $85 per hour = $340 ........................... $0 $340



### We have received no definitive data that would enable us to provide a cost
estimate for the corrective actions specified in this AD.

Authority for This Rulemaking

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

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

action.

Regulatory Findings

This AD will not have federalism implications under Executive Order


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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**

■ 

### 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):

2014–07–01 The Boeing Company: Amendment 39–17815; Docket No. FAA–2013–0425; Directorate Identifier

2012–NM–224–AD.

(a) Effective Date

This AD is effective June 3, 2014.

(b) Affected ADs

This AD affects AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010).

(c) Applicability

This AD applies to 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, as identified in Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition
This AD was prompted by reports of cracking in particular areas of the bulkhead structure at body station (BS) 2598. We are issuing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity of the bulkhead and the horizontal stabilizer support structure, and result in loss of controllability of the airplane.

(f) Compliance

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

(g) Inspections of the Bulkhead (Support Frame)

For airplanes on which the bulkhead (support frame) modification specified in Boeing Service Bulletin 747–53A2473 or Boeing Alert Service Bulletin 747–53A2837 has not been done, and on which an interim modification or aft inner chord repair specified in Boeing Alert Service Bulletin
747–53A2427 has not been done: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, except as provided by paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do an open-hole and surface high frequency eddy current (HFEC) inspection for cracking in the bulkhead (support frame), which includes the bulkhead splice fitting, frame supports, forward and aft inner chords, floor supports, and upper and lower web panels; do a surface HFEC inspection for cracking in the bulkhead upper web assembly; do an open-hole and surface HFEC inspection for cracking in the bulkhead lower web assembly; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, except as required by paragraphs (h), (m)(4), (m)(5), and (m)(6) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections, thereafter, at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013. Doing the modification required by paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.

(h) Interim Modification

For airplanes in Groups 1 and 2, as identified in Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, on which no cracking was found during any inspection required by paragraph (g) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, except as provided by paragraph (m)(2) of this AD, do the interim modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013. Doing the
interim modification terminates the repetitive inspections required by paragraph (g) of this AD in the area of the modification only. The repetitive inspections of the bulkhead lower web, as specified in paragraph (g) of this AD, must be done. If the aft inner chord repair or upper web repair specified in Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, has been accomplished, an interim modification on the side of the airplane that has the repair is not required by this paragraph.

(i) Post-Repair Inspection or Post-Interim Modification Inspection

For airplanes on which an interim modification, aft inner chord repair, or upper web repair has been done, as specified in paragraph (g) or (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, except as specified in paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, except as required by paragraph (m)(4) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013. Doing the modification required by paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.

(1) Do forward side surface HFEC inspections for cracking of the bulkhead forward inner chord, splice fitting, and frame support.

(2) Do surface and open-hole HFEC inspections for cracking in the repaired and modified areas of the bulkhead, as applicable.

(j) Bulkhead (Support Frame) Modification and Inspections

For airplanes on which the bulkhead (support frame) modification, as specified in Boeing Service Bulletin 747–53A2473 has
not been done as of the effective date of this AD: At the applicable time specified in tables 2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do the bulkhead (support frame) modification and inspections and all applicable related investigative and corrective actions; in accordance with steps 3.B.3., 3.B.4., and 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Doing the modification in this paragraph terminates the inspections required by paragraphs (g) and (i) of this AD.

(k) Post-Modification Inspections

(1) For airplanes on which the bulkhead (support frame) modification, as specified in Boeing Service Bulletin 747–53A2473 has been done: Except as provided by paragraphs (m)(7) and (m)(8) of this AD, at the applicable


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time specified in tables 6, 7, 8, and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do support frame post-modification inspections, and open-hole HFEC inspections for cracking in the hinge support, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in tables 6, 7, 8, and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,

2011.

(2) For airplanes on which the support frame modification, as specified in Boeing Service Bulletin 747–53A2473, Revision 1, dated February 20, 2007 (which is not incorporated by reference in this AD), has been done: Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at the applicable time specified in tables 4 and 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time general visual inspection of the frame web and upper shear deck (floor support) chord aft side for fasteners that were installed as part of an inner chord repair removal; and a one-time general visual inspection of the upper forward inner chord, frame support fitting, and splice fitting for the installation of certain fasteners; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions at the applicable times specified in tables 4 and 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011.

(3) For airplanes on which the support frame modification, as specified in Boeing Service Bulletin 747–53A2473, dated March 24, 2005 (which was incorporated by reference in AD 2006–05–06, Amendment 39–14503 (71 FR 12125, March 9, 2006)), has been done: Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at the applicable time specified in tables 5 and 10 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time general visual inspection of the upper forward inner chord, frame support fitting, and splice fitting for the installation of certain fasteners; a one-time general visual inspection for any repair installed on the left and right side of the aft inner chord; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions at the applicable times specified in tables 5 and 10 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011.

(4) For airplanes on which a postmodification inspection was done using paragraph 3.B.8. of Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 3, dated July 14, 2011 (which is not incorporated by reference in this AD): Except as required by paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in table 11 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time surface HFEC inspection of the support frame outer chord for cracking, in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011. If any cracking is found, repair before further flight, using a method approved in accordance with the procedures specified in paragraph (q) of
this AD.

(l) Post-Modification and Post-Repair Inspections

For airplanes on which cracking was found during a post-modification inspection and was repaired by doing the installation of an upper or lower corner post-modification web crack repair, as specified in Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011: At the applicable times specified in tables 6 and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,2011, do a bulkhead (support frame) postrepair inspection, and do all applicable corrective actions, in accordance with paragraph a., b., or c. of Part 4 of paragraph 3.B.8 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, as applicable, except as required by paragraph (m)(4) of this AD. Repeat the inspection, thereafter, at the applicable times specified in tables 6 and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,

2011.

(m) Exceptions to Service Information

(1) Where Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, specifies a compliance time after ‘‘the date on Revision 2 of this service bulletin,’’ this AD requires compliance within the specified compliance time after August 28, 2001 (the effective date of AD 2001–15–03, Amendment 39–12337 (66 FR 38365, July 24, 2001)).

(2) Where Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, specifies a compliance time after ‘‘the date on Revision 4 of this service bulletin,’’ this AD requires compliance within the specified compliance time after August 5, 2010 (the effective date of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010)).

(3) Where Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, specifies a compliance time ‘‘after the date on the respective service bulletin revision’’ this AD requires compliance within the specified compliance time after the
effective date of this AD.

(4) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013; or Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011; specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (q) of this AD.

(5) If, during any inspection required by paragraph (g) of this AD, any cracking is found in the bonded web doubler, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (q) of this AD.

(6) Where Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, specifies accomplishing inspections for cracking in the forward and aft inner chords, splice fittings, floor supports, and upper and lower web panels, this AD also requires doing an open-hole HFEC inspection of the bonded web doubler if present.

(7) Where Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, specifies a compliance time ‘‘after the date on Revision 2 of this service bulletin,’’ this AD requires compliance within the specified compliance time as of August 5, 2010 (the effective date of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010)).

(8) Where Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, specifies a compliance time ‘‘after the date on Revision 3 of this service bulletin,’’
or ‘‘after the date on Revision 4 of this service bulletin,’’ this AD requires compliance within the specified compliance time ‘‘after
the effective date of this AD.’’

(n) Optional Terminating Modification

Accomplishing the modification of the
bulkhead at BS 2598 in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2837, dated July 13, 2012, terminates the requirements of paragraphs (g), (h), (i), (j), (k), and (l) of this AD, except where Boeing Alert Service Bulletin 747–53A2837, dated July 13, 2012, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (q) of
this AD.

(o) Terminating Action for Certain Requirements of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010)

(1) Accomplishing the inspections, repairs,
and modification in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, is an acceptable terminating action for the corresponding inspections, repairs, and modification at the BS 2598 support frame required by paragraphs (i), (j), (k), (1), (m), (n), (o), (p), (q), (r), (s), (t), (u), and (v) of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010). Where Boeing Service Bulletin 747–


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53A2473, Revision 4, dated December 1, 2011, specifies to contact Boeing for repair instructions, the repair instructions must be approved in accordance with the procedures specified in paragraph (q) of this AD. All provisions of AD 2010–14–07 that are not specifically referenced in this paragraph remain fully applicable and must be complied with.

(2) Accomplishing the inspections, repairs,
and interim modification in accordance with Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, is an acceptable terminating action for the corresponding inspections, repairs and
interim modification at the BS 2598 bulkhead required by paragraphs (i), (j), (o), (s), (t), (u), and (v) of AD 2010–14–07, Amendment 39– 16352 (75 FR 38001, July 1, 2010). Where Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, specifies to contact Boeing for repair data, the repair data must be approved in accordance with the procedures specified in paragraph (q) of this AD. All provisions of AD 2010–14–07 that are not specifically referenced in this paragraph remain fully applicable and must be complied with.

(p) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraphs (g), (h), (i), and (n)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747– 53A2427, Revision 6, dated July 14, 2011, provided that the additional actions added in Boeing Alert Service Bulletin 747–53A2427, Revision 7, dated July 19, 2013, are done within the applicable compliance times specified in paragraphs (g), (h), and (i) of this AD. Boeing Alert Service Bulletin 747– 53A2427, Revision 6, dated July 14, 2011, is not incorporated by reference in this AD.

(q) 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 paragraph (r)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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) Related portions or applicable paragraphs of AMOCs approved previously in accordance with AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010), are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), (i), (j), (k), and (l) of this AD. All new actions specified in paragraphs (g), (h), (i), (j), (k), and (l) of this AD that are not identified in a previously approved AMOC must still be

done.

(r) Related Information

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

(2) Service information identified in this AD that is not incorporated by reference in this AD may be viewed at the addresses specified in paragraphs (s)(3) and (s)(4) of

this AD.

(s) Material Incorporated by Reference

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

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

(i) Boeing Alert Service Bulletin 747– 53A2427, Revision 7, dated July 19, 2013.

(ii) Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011.

(iii) Boeing Alert Service Bulletin 747– 53A2837, dated July 13, 2012.

(3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680;

Internet https://www.myboeingfleet.com.

(4) You may view this service information at 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 March

17, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–07339 Filed 4–28–14; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0020; Directorate Identifier 2013–CE–039–AD; Amendment**  **39–17821; AD 2014–07–07]**

**RIN 2120–AA64**



### Airworthiness Directives; British **Aerospace (Operations) Limited Airplanes** 

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an airworthiness directive (AD) 87–02–04 for British Aerospace (Operations) Limited Model HP.137 Jetstream MK.1, Jetstream Series 200, and Jetstream Series 3101 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct
an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking of the forward main landing gear yoke pintle resulting from corrosion pits leading to stress corrosion. We are issuing this AD to require actions to address the unsafe condition on these products.

**DATES** 

### : This AD is effective June 3, 2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 3, 2014.

**ADDRESSES** 

### : You may examine the AD
docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0020; 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 20590.

For service information identified in this AD, contact BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 1292 675207, fax: +44 1292 675704; email: RApublications@baesystems.com;

Internet: http:// www.jetstreamcentral.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.