16606 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules 

loose, replace the affected bearing with an 

airworthy bearing. 

(2) For Model MBB–BK 117 C–2 

helicopters: 

(i) Within the next 100 hours TIS or at the 

next annual inspection, whichever occurs 

first, modify the LH and RH guidance units 

and the lateral control lever by installing 

bushings and washers to prevent shifting of 

the bearings in the axial direction as follows: 

(A) Remove and disassemble the RH 

guidance unit and install a bushing, P/N 

L672M1012260, between the lever and the 

bracket as depicted in Detail B of Figure 4 of 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–67A–010, Revision 3, dated 

February 8, 2010 (BK117 ASB). Remove and 

disassemble the LH guidance unit and install 

a bushing, P/N L672M1012260, between the 

lever and the bracket as depicted in Detail C 

of Figure 4 of BK117 ASB. 

(B) Remove the lateral control lever and 

install new bushings in accordance with the 

Accomplishment Instructions, paragraphs 

3.C(9)(a) through 3.C(9)(g), of BK 117 ASB. 

(C) Identify the modified lever assembly by 

writing ‘‘MBB BK117 C–2–67A–010’’ on the 

lever with permanent marking pen and 

protect with a single layer of lacquer (CM 421 

or equivalent). 

(D) Apply corrosion preventive paste (CM 

518 or equivalent) on the shank of the screws 

and install airworthy parts as depicted in 

Figure 5 of BK117 ASB. 

(E) At intervals not to exceed 600 hours 

TIS or 24 months, whichever occurs first, 

inspect the bearings in the RH guidance unit, 

LH guidance unit, and lateral control 

guidance unit for play. If any bearing is loose, 

replace the affected bearing with an 

airworthy bearing. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0058, dated March 30, 2010. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–0674. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710, Main Rotor Control. 

Issued in Fort Worth, Texas, on March 18, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–06806 Filed 3–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0498; Directorate 

Identifier 2014–NM–152–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2007–16– 

08, which applies to all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–300, 747–400, 747–400D, and 

747SR series airplanes. AD 2007–16–08 

currently requires repetitive inspections 

for cracking of the station 800 frame 

assembly, and repair if necessary. Since 

we issued AD 2007–16–08, we have 

received additional reports of cracks 

found at the forward and aft inner chord 

strap and angles on the station 800 

frame on the left-side and right-side 

main entry doors. This proposed AD 

would expand the inspection area. We 

are proposing this AD to detect and 

correct fatigue cracks that could extend 

and fully sever the frame, which could 

result in development of skin cracks 

that could lead to rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 14, 2015. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. It is also available 

on the Internet at http://www.

regulations.gov by searching for and 

locating Docket No. FAA–2015–0498. 

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–2015– 

0498; 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 proposed 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0498; Directorate Identifier 

2014–NM–152–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules 16607 

Discussion 

On July 30, 2007, we issued AD 2007– 

16–08, Amendment 39–15147 (72 FR 

44728, August 9, 2007), for all The 

Boeing Company Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–300, 747–400, 747–400D, and 

747SR series airplanes. AD 2007–16–08 

requires repetitive inspections for 

cracking of the station 800 frame 

assembly, and repair if necessary. AD 

2007–16–08 resulted from several 

reports of cracks of the station 800 frame 

assembly on airplanes that occurred 

sooner than previously anticipated. We 

issued AD 2007–16–08 to detect and 

correct fatigue cracks that could extend 

and fully sever the frame, which could 

result in development of skin cracks 

that could lead to rapid 

depressurization of the airplane. 

Actions Since AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, 

August 9, 2007), Was Issued 

Since we issued AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, 

August 9, 2007), we received additional 

reports of cracking found at the forward 

and aft inner chord strap and angles on 

the station 800 frame on the left-side 

and right-side main entry doors. These 

cracks are outside the inspection area of 

AD 2007–16–08. We have determined 

that additional inspections are needed. 

This proposed AD would expand the 

inspection area to include the station 

800 frame between stringer 18 and 

stringer 30. 

Related Service Information Under 1 

CFR part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014. The service 

information describes procedure for 

inspecting and repairing cracking of the 

door number 2 forward edge frame 

assembly at body station 800. Refer to 

this service information for information 

on the procedures and compliance 

times. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

FAA’s Determination 

We are proposing 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. 

Proposed AD Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2007–16–08, Amendment 39–15147 (72 

FR 44728, August 9, 2007), this 

proposed AD would retain certain 

requirements of AD 2007–16–08. Those 

requirements are referenced in the 

service information identified 

previously, which, in turn, is referenced 

in paragraphs (g) and (h) of this 

proposed AD. This proposed AD would 

require additional inspections. This 

proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

Where Boeing Alert Service Bulletin 

747–53A2451, Revision 2, dated June 

13, 2014, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, this proposed 

AD would require repairing those 

conditions in one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 124 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts 

cost Cost per product Cost on U.S. operators 

Repetitive inspections.Up to 53 work-hours × $85 per hour = 

$4,505 per inspection cycle.

$0 Up to $4,505 per inspection 

cycle.

Up to $558,620 per inspection 

cycle 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
16608 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules 

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) 

2007–16–08, Amendment 39–15147 (72 

FR 44728, August 9, 2007), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–0498; Directorate Identifier 2014– 

NM–152–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 14, 2015. 

(b) Affected ADs 

This AD replaces AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, August 

9, 2007). 

(c) Applicability 

This AD applies to all Boeing Model 747– 

100, 747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–300, 747–400, 747–400D, and 

747SR series airplanes, certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found on the station 800 frame on the leftside and right-side main entry doors (MED), 

at the forward and aft inner chord strap and 

angles, which are outside the inspection area 

of AD 2007–16–08, Amendment 39–15147 

(72 FR 44728, August 9, 2007). We are 

issuing this AD to detect and correct fatigue 

cracks that could extend and fully sever the 

frame, which could result in development of 

skin cracks that could lead to rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of Station 800 Frame 

Assembly Between Stringer 14 and Stringer 

30 

Except as required by paragraph (i) of this 

AD, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2451, 

Revision 2, dated June 13, 2014: Do a 

detailed inspection for cracking in the inner 

chord strap, angles, and exposed web 

adjacent to the inner chords, and do surface 

and open hole high-frequency eddy current 

(HFEC) inspections for cracking in the inner 

chord strap and angles of the station 800 

frame assembly between stringer 14 and 

stringer 30, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014. Repeat the inspections 

at the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2451, Revision 2, dated 

June 13, 2014. 

(h) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(i) Exception to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2451, Revision 2, dated June 13, 

2014, specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

time after the effective date of this AD. 

(2) The Condition column of paragraph 

1.E., ‘‘Compliance,’’ of the Boeing Alert 

Service Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014, refers to total flight 

cycles ‘‘as of the Revision 2 date of this 

service bulletin.’’ This AD, however applies 

to airplanes with the specified total flight 

cycles or total flight hours as of the effective 

date of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and repairs of the inner chord 

strap and angles of the station 800 frame 

assembly between stringer 14 and stringer 18 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2451, Revision 1, 

dated November 10, 2005. 

(k) 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 (k)(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) AMOCs approved for AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, August 

9, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on March 

19, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07081 Filed 3–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0676; Directorate 

Identifier 2014–NM–164–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model BD–700–1A10 

and BD–700–1A11 airplanes. This 

proposed AD was prompted by a report 

of several events where pilots 

experienced difficulty in lateral control 

of the airplane after doing a climb 

through heavy rain conditions and a 

determination that the cause was water 

ingress in the aileron control pulley 

assembly. This proposed AD would 

require, for certain airplanes, inspecting 

for correct clearance and rework if 

necessary, and, for certain other 

airplanes, installing a cover for the 

aileron pulley assembly. We are 

proposing this AD to prevent water 

ingress in the aileron control pulley 

assembly, which could freeze in cold 

conditions and result in reduced control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 14, 2015. 


tkelley on DSK3SPTVN1PROD with PROPOSALS