Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41117 

(e) Reason 

This AD was prompted by a report of a 

BWH system failing to activate when the beta 

mode was triggered. We are issuing this AD 

to prevent the inadvertent activation of 

ground beta mode during flight, which could 

lead to engine overspeed, engine damage or 

failure, and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Terminating Modification 

Within 6,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD: Modify the BWH microswitch 

installation by replacing the existing BWH 

microswitch installation bracket with a new 

bracket having part number 87610164–003, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–76–33, dated December 13, 2012. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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 

Transport Canada Civil Aviation (TCCA); or 

Bombardier’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–01R1, 

dated March 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1025-0002. 

(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) Bombardier Service Bulletin 8–76–33, 

dated December 13, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(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. 2014–15952 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–2014–0395; Directorate 

Identifier 2014–SW–016–AD; Amendment 

39–17876; AD 2014–06–51] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Airbus Helicopters) (Type Certificate 

Previously Held by Eurocopter 

Deutschland GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Airbus 

Helicopters Model MBB–BK 117 A–3, 

MBB–BK 117 A–4, MBB–BK 117 B–1, 

and MBB–BK 117 C–2 helicopters with 

a certain Metro Aviation, Inc. (Metro), 

vapor-cycle air conditioning kit pulley 

(pulley) installed, which was sent 

previously to all known U.S. owners 

and operators of these helicopters. This 

AD supersedes AD 2013–12–06, which 

required inspecting the pulley for 

looseness and properly installed 

lockwire and re-installing the pulley. 

Since we issued AD 2013–12–06, we 

received a report of a possible design 

and manufacturing deficiency in some 

pulleys wherein they did not have 

sufficient thread depth, allowing the 

pulley to detach from the rotor brake 

disc. This AD requires inspecting each 

pulley attaching bolt hole to determine 

if there is sufficient depth of the threads 

and either removing the pulley if the 

depth is insufficient or installing dual 

locking tabs under each pulley attaching 

bolt if the depth is sufficient. These 

actions are intended to prevent the 

pulley from detaching, resulting in 

damage to the tail rotor (T/R) driveshaft, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

30, 2014 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

(EAD) 2014–06–51, issued on March 24, 

2014, which contains the requirements 

of this AD. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 30, 2014. 

We must receive comments on this 

AD by September 15, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the economic 

evaluation, any incorporated by 

reference service information, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this AD, contact Metro Aviation, Inc., 


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1214 Hawn Ave, Shreveport, LA 71107; 

phone: (318) 222–5529; Web site: 

metroproductsupport.com. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: 

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 prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On June 13, 2013, we issued AD 

2013–12–06, Amendment 39–17484 (78 

FR 40956, July 9, 2013) (AD 2013–12– 

06), for Eurocopter Deutschland GmbH 

(now Airbus Helicopters) Model MBB– 

BK 117 A–3, MBB–BK 117 A–4, MBB– 

BK 117 B–1, and MBB–BK 117 C–2 

helicopters with a Metro vapor-cycle air 

conditioning kit installed in accordance 

with Supplemental Type Certificate No. 

SH3880SW. AD 2013–12–06 required 

repetitively inspecting the air 

conditioning drive pulley for looseness 

and properly installed lockwire, and 

also required reinstalling the pulley. AD 

2013–12–06 resulted from two reports of 

the pulley detaching from the rotor 

brake disk on the T/R driveshaft. We 

issued AD 2013–12–06 to prevent 

separation of the pulley, damage to the 

T/R driveshaft, and subsequent loss of 

control of the helicopter. 

Actions Since AD 2013–12–06 Was 

Issued 

After we issued AD 2013–12–06, 

Metro developed a procedure to install 

a tabbed washer underneath the bolt 

heads securing the pulley to the rotor 

disc. This procedure was intended to 

provide a secondary locking feature to 

the bolts, and to relieve the requirement 

for repetitive inspections of the safety 

wire which secures the bolts. On 

December 20, 2013, Metro requested 

and we approved this procedure as a 

global Alternative Method of 

Compliance (AMOC) for AD 2013–12– 

06 in lieu of performing the repetitive 

inspections required by paragraph (e) of 

that AD. 

On March 10, 2014, we received a 

report that an attaching bolt would not 

seat on the mating surface of the pulley. 

Compliance with the AMOC revealed a 

possible design deficiency and a 

manufacturing defect in some pulleys. 

Metro has determined that the pulley, 

along with two additional pulleys from 

other helicopters, did not have 

sufficient thread depth. This condition 

may allow the attaching bolts to come 

loose, resulting in the pulley detaching 

from the rotor brake disc, subsequent 

damage to the T/R driveshaft, and loss 

of control of the helicopter. 

On March 24, 2014, we issued EAD 

2014–06–51, which superseded AD 

2013–12–06, for those to whom it was 

made immediately effective. EAD 2014– 

06–51 requires inspecting the pulley to 

determine if there is sufficient depth of 

the threads and removing the pulley if 

there is not sufficient depth. EAD 2014– 

06–51 also requires installing a dual 

locking tab on each pulley attaching bolt 

and reporting the inspection findings to 

the FAA. Finally, EAD 2014–06–51 

revises the applicability to helicopters 

with a pulley, P/N 30001, installed 

rather than with the air conditioning kit 

installed because this pulley has been 

determined to be the unsafe condition. 

EAD 2014–06–51 was sent previously to 

all known U.S. owners and operators of 

these helicopters. The actions in EAD 

2014–06–51 are intended to prevent the 

pulley detaching from the rotor brake 

disc, subsequent damage to the T/R 

driveshaft, and loss of control of the 

helicopter. 

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 these same 

type designs. 

Related Service Information 

We reviewed Metro Alert Service 

Bulletin (ASB) No. MA145–21B–003, 

Revision B, dated December 20, 2013 

(ASB MA145–21B–003), which 

describes procedures for installing a 

dual-locking tab on the air conditioning 

drive pulley attachment bolts. 

Since we issued EAD 2014–06–51, 

Metro released ASB No. MA145–21– 

004, Revision IR, dated March 24, 2014, 

which describes procedures for 

inspecting the air conditioning drive 

pulley thread depth. This AD continues 

to reference ASB MA145–21B–003. 

AD Requirements 

This AD requires, within 5 hours 

time-in-service, inspecting each pulley 

attaching bolt hole to determine if there 

is sufficient depth of the threads. If the 

depth is less than 0.61 inch, this AD 

requires removing the pulley. This AD 

also requires installing dual locking tabs 

under each pulley attaching bolt by 

following the Accomplishment 

Instructions, paragraphs 3.E. through 

3.G., of ASB MA145–21B–003. This AD 

also requires submitting a report of the 

inspection findings to the FAA. 

Differences Between This AD and the 

Service Information 

This AD requires determining the 

depth of the threaded portion of the 

pulley attaching bolt holes; the service 

information does not. 

Costs of Compliance 

We estimate that this AD will affect 

75 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. At an average labor rate of $85 

per work-hour, inspecting the pulley 

bolt holes, and installing the tabbed 

washers will require 6 work hours, and 

required parts will cost $100, for a cost 

per helicopter of $610 and a total cost 

of $45,750 for the fleet. 

Reviewing instructions, collecting and 

reviewing information, and submitting a 

report to the FAA will require 0.5 workhour, for a cost per helicopter of $43 

and a cost of $3,225 for the fleet. 

If necessary, replacing a pulley will 

require about 2 work-hours, and 

required parts would cost $800, for a 

total cost per helicopter of $970. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41119 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting required by this 

AD is mandatory. Comments concerning 

the accuracy of this burden and 

suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we found and continue to 

find that the risk to the flying public 

justifies waiving notice and comment 

prior to adopting this rule because the 

required corrective actions must be 

done within 5 hours time-in-service, a 

very short time period based on the 

average flight-hour utilization rate of 

these helicopters. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment before issuing this AD were 

impracticable and contrary to the public 

interest and that good cause existed to 

make the AD effective immediately by 

EAD 2014–06–51, issued on March 24, 

2014, to all known U.S. owners and 

operators of these helicopters. These 

conditions still exist and the AD is 

hereby published in the Federal 

Register as an amendment to section 

39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

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 

responsibilities among the various 

levels of government. 

For the reasons discussed, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 

removing Airworthiness Directive (AD) 

2013–12–06, Amendment 39–17484 (78 

FR 40956, July 9, 2013), and adding the 

following new AD: 

2014–06–51 Airbus Helicopters 

Deutschland GmbH (Airbus Helicopters) 

(Type Certificate Previously Held By 

Eurocopter Deutschland GmbH) 

Helicopters: Amendment 39–17876; 

Docket No. FAA–2014–0395; Directorate 

Identifier 2014–SW–016–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model MBB–BK 117 A–3, MBB–BK 117 A– 

4, MBB–BK 117 B–1, and MBB–BK 117 C– 

2 helicopters with a Metro Aviation, Inc., 

vapor-cycle air conditioning kit pulley 

(pulley) part number (P/N) 30001 installed in 

accordance with Supplemental Type 

Certificate (STC) No. SH3880SW. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

insufficient thread depth which could allow 

the attaching bolts to come loose, resulting in 

the pulley detaching from the rotor brake 

disc, subsequent damage to the tail rotor (T/ 

R) driveshaft, and loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective July 30, 2014 to 

all persons except those persons to whom it 

was made immediately effective by 

Emergency AD 2014–06–51, issued on March 

24, 2014, which contains the requirements of 

this AD. 

(d) Affected ADs 

This AD supersedes AD 2013–12–06, 

Amendment 39–17484 (78 FR 40956, July 9, 

2013). 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

Within 5 hours time-in-service, inspect 

each pulley attaching bolt hole to determine 

the depth: 

(1) Relieve tension from the compressor 

drive belt and remove each bolt that attaches 

the pulley to the rotor brake disc. Do not 

remove all three bolts at the same time. 

(2) Remove AN960–416 washer or MAI– 

145–DUAL LOCK TAB washer. 

(3) Using a bolt or screw with 1⁄4-28 threads 

with 0.5 inch of threads and a minimum of 

0.8 inch grip length, coat the shank with blue 

dye or permanent marker and thread into 

hole until threads have lightly bottomed 

(finger tight). Scribe the shank flush with the 

face of the rotor brake disk. Measure distance 

from end to scribe mark (length protruding 

into assembly). This dimension represents 

total depth of threads and stack-up of the 

brake disk. 

(4) If the depth measures less than 0.61 

inch, remove the pulley. 

(5) If the depth measures 0.61 inch or 

more, install dual locking tabs as described 

in the Accomplishment Instructions, 

paragraphs 3.E. through 3.G., of Metro 

Aviation, Inc., Alert Service Bulletin No. 

MA145–21B–003, Revision B, dated 

December 20, 2013. 

(g) Reporting Requirement 

Within 10 days after inspecting the pulley 

as required by paragraph (f)(3) of this AD, 

submit a report with the helicopter model, 

helicopter serial number, hole number 1 

thread depth, hole number 2 thread depth (if 

measured), and hole number 3 thread depth 


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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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