41120 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

(if measured) to the person identified in 

paragraph (h)(1) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5170; 

email 7-AVS-ASW-170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

(1) Metro Aviation, Inc., Alert Service 

Bulletin No. MA145–21–004, Revision IR, 

dated March 24, 2014, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Metro Aviation, Inc., 1214 

Hawn Ave., Shreveport, LA 71107; phone: 

(318) 222–5529; Web site: 

metroproductsupport.com. You may review a 

copy of the service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137. 

(2) STC No. SH3380SW, amended April 16, 

2004, may be found on the Internet at, http:// 

www.regulations.gov in Docket No. FAA– 

2014–0395. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6500: Tail Rotor Drive. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Metro Aviation, Inc., Alert Service 

Bulletin No. MA145–21B–003, Revision B, 

dated December 20, 2013. 

(ii) Reserved. 

(3) For Metro Aviation, Inc., service 

information identified in this AD, contact 

Metro Aviation, Inc., 1214 Hawn Ave, 

Shreveport, LA 71107; phone: (318) 222– 

5529; Web site: metroproductsupport.com. 

(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 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–16387 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–2014–0432; Directorate 

Identifier 2014–NM–099–AD; Amendment 

39–17898; AD 2014–14–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–07– 

01, for certain The Boeing Company 

Model 747 airplanes. AD 2014–07–01 

required repetitive inspections for 

cracking in certain bulkhead structure; 

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. 

This AD clarifies certain paragraph 

references and revises a compliance 

time. This AD was prompted by a 

determination that certain paragraph 

references are in error. 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 July 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 3, 2014 (79 FR 23893, April 

29, 2014). 

We must receive any comments on 

this AD by August 29, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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–2014– 

0432; 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 Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 

On March 17, 2014, we issued AD 

2014–07–01, Amendment 39–17815 (79 

FR 23893, April 29, 2014), for certain 

The Boeing Company Model 747 

airplanes. AD 2014–07–01 required 

repetitive inspections, including postrepair and post-modification 

inspections, for cracking in the 

bulkhead structure at body station (BS) 

2598; certain one-time inspections of 

certain fasteners and support frame 

modifications on certain airplanes; 

related investigative and corrective 


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actions, if necessary; and an interim 

modification that would terminate 

certain repetitive inspections. 

AD 2014–07–01, Amendment 39– 

17815 (79 FR 23893, April 29, 2014), 

resulted from 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. 

We issued AD 2014–07–01 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. 

Actions Since AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, 

April 29, 2014), Was Issued 

Paragraph (o)(1) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, 

April 29, 2014), terminated the actions 

in certain paragraphs of AD 2010–14– 

07, Amendment 39–16352 (75 FR 

38001, July 1, 2010). AD 2014–07–01, 

however, incorrectly terminated 

‘‘paragraphs (k) and (l),’’ which should 

have been ‘‘paragraph (k)(1).’’ Paragraph 

(o)(1) of this AD corrects that reference 

to ‘‘paragraph (k)(1).’’ All provisions of 

AD 2010–14–07 that are not specifically 

referenced in paragraph (o)(1) of this AD 

remain fully applicable and must be 

complied with, including paragraph 

(k)(2) of AD 2010–14–07. 

We also found an additional incorrect 

paragraph reference. The first sentence 

of paragraph (p) of AD 2014–07–01 

provides credit for the actions required 

by paragraphs (g), (h), (i), and (n)(2) of 

that AD. Paragraph (n)(2) of AD 2014– 

07–01 does not exist. The text of 

paragraph (p) of this AD has been 

revised to refer to paragraphs (g), (h), 

and (i) of this AD. 

We have also clarified that the 

airplanes affected by paragraph (i) of 

this AD include airplanes on which an 

interim modification, aft inner chord 

repair, or upper web repair has been 

previously accomplished as specified in 

Boeing Alert Service Bulletin 747– 

53A2427. 

Compliance Time Change for Airplanes 

in Groups 4 and 5 

We have moved the compliance time 

specified in paragraph (j) of 2014–07– 

01, Amendment 39–17815 (79 FR 

23893, April 29, 2014), into new 

paragraphs (j)(1) and (j)(2) of this AD. 

Paragraph (j)(1) of this AD restates the 

compliance times for airplanes in 

Groups 1, 2, and 3. Paragraph (j)(2) of 

this AD provides a new compliance 

time for airplanes in Groups 4 and 5. We 

have added a compliance time (grace 

period) of ‘‘18 months after the effective 

date of this AD’’ for airplanes in Groups 

4 and 5. We have determined that this 

new grace period will provide an 

acceptable level of safety. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

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. This AD 

provides clarification of certain 

paragraph references and revises a 

compliance time. 

FAA’s Justification and Determination 

of the Effective Date 

Since this AD merely corrects 

incorrect paragraph references and 

includes a relieving grace period for 

certain airplanes, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0432; Directorate Identifier 2014– 

NM–099–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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: 

ESTIMATED 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 the inspections 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: 


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ON-CONDITION COSTS

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 

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 part 39 of the Federal 

Aviation Regulations (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 

removing Airworthiness Directive (AD) 

2014–07–01, Amendment 39–17815 (79 

FR 23893, April 29, 2014) and adding 

the following new AD: 

2014–14–03 The Boeing Company: 

Amendment 39–17898; Docket No. 

FAA–2014–0432; Directorate Identifier 

2014–NM–099–AD. 

(a) Effective Date 

This AD is effective July 15, 2014. 

(b) Affected ADs 

This AD supersedes AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014). 

(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) Retained Inspections of the Bulkhead 

(Support Frame) With No Changes 

This paragraph restates the actions 

required by paragraph (g) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with no changes. 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 openhole 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 openhole 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) Retained Interim Modification With No 

Changes 

This paragraph restates the actions 

required by paragraph (h) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with no changes. 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 


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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) Retained Post-Repair Inspection or PostInterim Modification Inspection With a 

Clarification 

This paragraph restates the actions 

required by paragraph (i) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with a clarification of the affected 

airplanes. 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, or has been 

previously accomplished as specified in 

Boeing Alert Service Bulletin 747–53A2427: 

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) Retained Bulkhead (Support Frame) 

Modification and Inspections With a Revised 

Compliance Time 

This paragraph restates the actions 

required by paragraph (j) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with a revised compliance time. 

For airplanes on which the bulkhead 

(support frame) modification, as specified in 

Boeing Service Bulletin 747–53A2473 has 

not been done as of June 3, 2014 (the 

effective date of AD 2014–07–01): At the 

applicable time specified in paragraph (j)(1) 

or (j)(2) of this AD, 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. 

(1) For Groups 1, 2, and 3 airplanes 

identified in Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011: At the time specified in table 2 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011. 

(2) For Groups 4 and 5 airplanes identified 

in Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011: At the 

earlier of the times specified in paragraphs 

(j)(2)(i) and (j)(2)(ii) of this AD, 

(i) Before the accumulation of 20,000 total 

flight cycles or within 18 months after 

August 5, 2010 (the effective date of AD 

2010–14–07, Amendment 39–16352 (75 FR 

38001, July 1, 2010), whichever occurs later. 

(ii) Before the accumulation of 12,000 total 

flight cycles or within 18 months after the 

effective date of this AD, whichever occurs 

later. 

(k) Retained Post-Modification Inspections 

With No Changes 

This paragraph restates the actions 

required by paragraph (k) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with no changes. 

(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 

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) Retained Post-Modification and PostRepair Inspections With No Changes 

This paragraph restates the actions 

required by paragraph (l) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with no changes. For airplanes on 

which cracking was found during a postmodification 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– 


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41124 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

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) Retained Exceptions to Service 

Information With No Changes 

This paragraph restates the exceptions 

specified in paragraph (m) of AD 2014–07– 

01, Amendment 39–17815 (79 FR 23893, 

April 29, 2014), with no changes. 

(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 June 3, 

2014 (the effective date of AD 2014–07–01 

Amendment 39–17815 (79 FR 23893, April 

29, 2014)). 

(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 

June 3, 2014 (the effective date of AD 2010– 

14–07, Amendment 39–17815 (79 FR 23893, 

April 29, 2014)). 

(n) Retained Optional Terminating 

Modification With No Changes 

This paragraph restates the actions 

required by paragraph (n) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with no changes. 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) Retained Terminating Action for Certain 

Requirements of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010), With Revised Terminating Action 

This paragraph restates the terminating 

actions specified in paragraph (o) of AD 

2014–07–01, Amendment 39–17815 (79 FR 

23893, April 29, 2014), with revised 

terminating action within paragraph (o)(1) of 

this AD. 

(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– 

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, including paragraph (k)(2) of 

AD 2010–14–07. 

(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) Retained Credit for Previous Actions 

With Change to Paragraph Reference 

This paragraph restates the credit specified 

in paragraph (p) of AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), with a change to a paragraph 

reference. This paragraph provides credit for 

the actions required by paragraphs (g), (h), 

and (i) of this AD, if those actions were 

performed before June 3, 2014 (the effective 

date of AD 2014–07–01) 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 

for 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 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41125 

(g), (h), (i), (j), (k), and (l) of this AD that are 

not identified in a previously approved 

AMOC must still be done. 

(5) AMOCs approved for AD 2014–07–01, 

Amendment 39–17815 (79 FR 23893, April 

29, 2014), are approved as AMOCs for the 

corresponding provisions of this AD. 

(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)(4) and (s)(5) 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. 

(3) The following service information was 

approved for IBR on June 3, 2014 (79 FR 

23893). 

(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. 

(4) 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. 

(5) 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. 

(6) 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 July 3, 

2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–16381 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 91 and 135 

[Docket No. FAA–2010–0982; Amdt. No(s). 

91–330A, 135–129A] 

RIN 2120–AJ53 

Helicopter Air Ambulance, Commercial 

Helicopter, and Part 91 Helicopter 

Operations; Correction 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; Correction. 

SUMMARY: The FAA is correcting a final 

rule published on February 21, 2014. In 

that rule, the FAA amended its 

regulations to revise the helicopter air 

ambulance, commercial helicopter, and 

general aviation helicopter operating 

requirements. This document corrects 

errors in the codified text of that 

document. 

DATES: Effective April 22, 2015. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Andrew C. Pierce, Air 

Transportation Division, 135 Air Carrier 

Operations Branch, AFS–250, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone 202– 

267–8238; email andy.pierce@faa.gov. 

For legal questions concerning this 

action, contact Nancy Sanchez, 

Attorney, AGC–220, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone 202–267–3073; email 

nancy.sanchez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On February 21, 2014, the FAA 

published a final rule entitled, 

‘‘Helicopter Air Ambulance, 

Commercial Helicopter, and part 91 

Helicopter Operations’’ (79 FR 9932) 

(effective date delayed on April 21, 

2014, at 79 FR 22012). In that final rule, 

the FAA addressed helicopter air 

ambulance operations and all 

commercial helicopter operations 

conducted under part 135. The FAA 

also established new weather 

minimums for helicopters operating 

under part 91 in Class G airspace. 

The FAA is correcting § 91.155 and 

removing duplicative flight visibility 

requirements for part 91 helicopter 

operations in Class G airspace. Also, the 

FAA is correcting the regulatory text in 

§ 135.609 to delineate visual flight rule 

operations and instrument flight rules 

operations. Finally, the agency is 

correcting the regulatory text in 

§ 135.621(b) and clarifying the intended 

list of topics that must be included in 

the certificate holder’s FAA-approved 

medical personnel training program. 

Corrections 

In FR Doc. 35, beginning on page 

9932, in the Federal Register of 

February 21, 2014, make the following 

corrections: 

Corrections to Regulatory Text 

■ 1. On page 9973, in § 91.155, revise 

the entry ‘‘For helicopters: Day’’ in the 

table in paragraph (a) to read as follows: 

§ 91.155 Basic VFR weather minimums. 

(a) * * * 


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