Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / Proposed Rules 37337 

(m) New Repetitive Inspections and Repair 

At the applicable initial compliance times 

specified in paragraph (n) of this AD: Do the 

applicable actions specified in paragraph 

(m)(1) or (m)(2) of this AD, in accordance 

with Step 3 of Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 4, dated June 24, 

2010; or Boeing Alert Service Bulletin 757– 

54A0047, Revision 5, dated June 9, 2011. If 

no cracking is found, repeat the inspections 

thereafter at intervals not to exceed the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011. If any crack is found during any 

inspection required by this paragraph, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(1) For Group 1, Configuration 1 airplanes 

identified in Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011: Do the actions specified in paragraph 

(m)(1)(i) or (m)(1)(ii) of this AD. 

(i) Do a detailed inspection for cracking of 

the bulkhead in the area around the access 

door cutout and around the critical fasteners 

in the horizontal flange. 

(ii) Do a detailed inspection for cracking of 

the bulkhead in the area around the access 

door cutout and around the critical fasteners 

in the horizontal flange, and do an ultrasonic 

inspection for cracking of the bulkhead 

around the fasteners in the horizontal flange. 

Doing the actions in this paragraph extends 

the repetitive intervals of the inspections 

required by paragraph (n) of this AD. 

(2) For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: Do a detailed 

inspection for cracking of the bulkhead in the 

area around the access door cutout and 

around the critical fasteners in the horizontal 

flange. 

(n) New Compliance Times for Paragraph 

(m) of This AD 

At the applicable times specified in 

paragraphs (n)(1) and (n)(2) of this AD, do the 

actions required by paragraph (m) of this AD. 

(1) For Group 1, Configuration 1 airplanes 

identified in Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011: At the later of the times specified in 

paragraph (n)(1)(i) or (n)(1)(ii) of this AD. 

(i) Within 1,800 flight cycles after 

accomplishing the most recent inspection 

required by paragraph (h) or (j) of this AD. 

(ii) Within 90 days after the effective date 

of this AD. 

(2) For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: At the later 

of the times specified in paragraph (n)(2)(i) 

or (n)(2)(ii) of this AD. 

(i) Within 3,000 flight cycles after 

accomplishing the most recent inspection 

required by paragraph (h) or (j) of this AD. 

(ii) Within 90 days after the effective date 

of this AD. 

(o) New Terminating Action for Certain 

Airplanes: Fastener Replacement 

For Group 1, Configuration 2 airplanes; 

and Group 2 airplanes; as identified in 

Boeing Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011: Within 9,000 

flight cycles or 54 months after the effective 

date of this AD, whichever occurs first, 

replace the horizontal and vertical flange 

fasteners in the strut-to-diagonal brace fitting 

on the number 1 and number 2 struts with 

new fasteners and do all related investigative 

and applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–54A0047, Revision 5, dated June 9, 

2011, except where Boeing Alert Service 

Bulletin 757–54A0047, Revision 5, dated 

June 9, 2011, specifies to contact Boeing for 

repair instructions, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (q) of this AD. Do all related 

investigative and corrective actions before 

further flight. Accomplishment of the actions 

required in paragraph (o) of this AD 

terminates the inspection requirements of 

paragraphs (g), (h), (j), and (m) of this AD for 

Group 1, Configuration 2 airplanes; and 

Group 2 airplanes; as identified in Boeing 

Alert Service Bulletin 757–54A0047, 

Revision 5, dated June 9, 2011. 

(p) Credit for Previous Actions 

(1) Except for the actions specified in 

paragraphs (j), (m), and (o) of this AD, this 

paragraph provides credit for the actions 

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

if those actions were done before March 18, 

2008 (the effective date of AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), using Boeing Service Bulletin 757– 

54A0047, Revision 1, dated March 24, 2005; 

or Boeing Alert Service Bulletin 757– 

54A0047, Revision 2, dated January 31, 2007. 

(2) This paragraph provides credit for the 

initial inspection required by paragraph (h) 

of this AD, if that inspection was done before 

June 29, 2005 (the effective date of AD 2005– 

12–04, Amendment 39–14120 (70 FR 34313, 

June 14, 2005)), using the actions required by 

paragraph (b) or (d), as applicable, of AD 

2004–12–07, Amendment 39–13666 (69 FR 

33561, June 16, 2004). 

(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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 previously in 

accordance with AD 2004–12–07, 

Amendment 39–13666 (69 FR 33561, June 

16, 2004), are approved as AMOCs for the 

corresponding provisions of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2005–12–04, 

Amendment 39–14120 (70 FR 34313, June 

14, 2005), are approved as AMOCs for the 

corresponding provisions of this AD. 

(6) AMOCs approved previously in 

accordance with AD 2007–16–13, 

Amendment 39–15152 (72 FR 44753, August 

9, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(7) AMOCs approved previously in 

accordance with AD 2008–05–10, 

Amendment 39–15404 (73 FR 11347, March 

3, 2008), are approved as AMOCs for the 

corresponding provisions of this AD. 

(r) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone 425–917–6440; fax 425– 

917–6590; email: Nancy.Marsh@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, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; Internet: https://www.myboeingfleet.

com. You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on June 14, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15181 Filed 6–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0643; Directorate 

Identifier 2011–NM–190–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
37338 Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Fokker Services 

B.V. Model F.28 Mark 0070 and 0100 

airplanes. The existing AD currently 

requires performing a detailed visual 

inspection for cracks of the pistons on 

the main landing gear (MLG), and 

replacing the affected pistons if 

necessary. Since we issued that AD, a 

new modification has been developed to 

safeguard the integrity of the MLG 

assembly and improve surface 

protection of the affected area of the 

MLG piston. This proposed AD would 

also require modifying the MLG by 

installing a piston containing a certain 

part number, and revising the aircraft 

maintenance program. We are proposing 

this AD to prevent MLG failure, possibly 

resulting in loss of control of the 

airplane during the landing roll-out. 

DATES: We must receive comments on 

this proposed AD by August 6, 2012. 

ADDRESSES: You may send comments 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, between 9 

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

Friday, except Federal holidays. 

For Fokker service information 

identified in this proposed AD, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 231, 2150 AE 

Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@

stork.com; Internet http:// 

www.myfokkerfleet.com. For Goodrich 

service information identified in this 

proposed AD, contact Goodrich, 1400 

South Service Road, West Oakville, L6L 

5Y7, Ontario, Canada, telephone +1– 

905–827–7777; fax +1–905–825–1583; 

Internet http://www.goodrich.com/ 

TechPubs. You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. 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; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1137; fax 425–227–1149. 

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–2012–0643; Directorate Identifier 

2011–NM–190–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 based on 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. 

Discussion 

On January 31, 2011, we issued AD 

2011–04–01, Amendment 39–16601 (76 

FR 8618, February 15, 2011). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, 

February 15, 2011), a new modification 

has been developed to safeguard the 

integrity of the MLG assembly and 

improve surface protection of the 

affected area of the MLG piston. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0159, 

dated August 26, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During a normal walk around check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG piston. The affected MLG unit had 

accumulated 7,909 flight cycles (FC) at the 

time of detection. The piston was sent to 

Goodrich, the landing gear manufacturer, for 

detailed investigation, which revealed that 

the crack had been initiated by corrosion 

pits. The extent of the corrosion indicates 

that the initial crack existed for a substantial 

period before a high loading event caused the 

crack to grow further by ductile overload. 

This condition, if not detected and 

corrected, could lead to MLG failure during 

the landing roll-out, possibly resulting in 

damage to the aeroplane and injury to 

occupants. 

To address this potential unsafe condition, 

EASA issued AD 2009–0221 [which 

corresponds with FAA AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, February 

15, 2011)] to require a one-time detailed 

visual inspection of the MLG pistons, the 

replacement of any MLG pistons on which 

cracks are detected, and the reporting of all 

findings to the aeroplane TC [type certificate] 

holder. No cracks were reported as a result 

of this inspection. 

Subsequently, a repetitive inspection was 

introduced in the Airworthiness Limitations 

Section (Fokker Services report SE–623 Issue 

8) in Appendix 1 of the Maintenance Review 

Board (MRB) document to safeguard the 

integrity of the MLG assembly, pending the 

accomplishment of a terminating action. 

Goodrich issued Service Bulletin (SB) 

41000–32–29 to introduce an improved 

surface protection (nickel plate) of the 

affected area of the MLG piston P/N [part 

number] 41141–3 and re-identification as 

P/N 41141–5, which is considered as a 

terminating action for the repetitive 

inspections. 

For the reasons described above, this 

[EASA] AD requires repetitive visual 

inspections of the P/N 41141–3 MLG piston 

for cracks and, depending on findings, 

replacement or modification of the MLG 

piston. This [EASA] AD also requires 

modification of the affected MLG by 

installing a piston P/N 41141–5. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF100–32– 

161, dated April 7, 2011; and Fokker 

Engineering Report, MRB Appendix 1, 

SE–623, Issue 8, dated March 17, 2011. 

Goodrich Aerospace Canada Ltd. has 

issued Goodrich Service Bulletin 

41000–32–29, dated November 10, 2010. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / Proposed Rules 37339 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 2 products of U.S. registry. 

The actions that are required by AD 

2011–04–01, Amendment 39–16601 (76 

FR 8618, February 15, 2011), and 

retained in this proposed AD take about 

3 work-hours per product, at an average 

labor rate of $85 per work hour. Based 

on these figures, the estimated cost of 

the currently required actions is $255 

per product. 

We estimate that it would take about 

26 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$4,420, or $2,210 per product. 

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 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 this 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2011–04–01, Amendment 39–16601 (76 

FR 8618, February 15, 2011), and adding 

the following new AD: 

Fokker Services B.V.: Docket No. FAA– 

2012–0643; Directorate Identifier 2011– 

NM–190–AD. 

(a) Comments Due Date 

We must receive comments by August 6, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, February 

15, 2011). 

(c) Applicability 

(1) This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes; 

certificated in any category; all serial 

numbers, equipped with Goodrich (formerly 

Menasco, Colt Industries) main landing gear 

(MLG) units, part numbers (P/N) 41050–7, 

41050–8, 41050–9, 41050–10, 41050–11, 

41050–12, 41050–13, 41050–14, 41050–15, 

41050–16, 41060–1, 41060–2, 41060–3, 

41060–4, 41060–5 or 41060–6. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections). Compliance 

with these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these actions, the 

operator may not be able to accomplish the 

actions described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (n)(1) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Main Landing Gear. 

(e) Reason 

This AD was prompted by a new 

modification developed to safeguard the 

integrity of the MLG assembly and improve 

surface protection of the affected area of the 

MLG piston. We are issuing this AD to 

prevent MLG failure, possibly resulting in 

loss of control of the airplane during the 

landing roll-out. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Initial Inspection 

This paragraph restates the initial 

inspection required by paragraph (g) of AD 

2011–04–01, Amendment 39–16601 (76 FR 

8618, February 15, 2011). Within 30 days 

after March 22, 2011 (the effective date of AD 

2011–04–01), do a detailed visual inspection 

for cracks of the MLG pistons, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–32–158, 

dated October 2, 2009. 

(h) Retained Replacement 

This paragraph restates the replacement 

required by paragraph (h) of AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, February 

15, 2011). If any cracked MLG piston is found 

during the inspection required by paragraph 

(g) of this AD, before further flight, replace 

the affected piston with a serviceable part, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009. 

(i) New Requirement: Modification 

Within 120 months, or during a scheduled 

overhaul of the MLG, whichever occurs first 

after the effective date of this AD: Modify the 

MLG by installing a piston containing P/N 

41141–5, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–161, dated April 

7, 2011. Re-installation of a MLG piston 

which has been modified and re-identified as 

P/N 41141–5, in accordance with the 

Accomplishment Instructions of Goodrich 

Service Bulletin 41000–32–29, dated 

November 10, 2010, is an optional method of 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
37340 Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / Proposed Rules 

compliance for the requirements in this 

paragraph of this AD. It is acceptable to 

operate an airplane with one MLG having a 

P/N 41141–5 piston installed, and the other 

MLG having a P/N 41141–3 piston installed, 

provided all MLG P/N 41141–3 are replaced 

within the compliance times specified in 

paragraph (i) of this AD. 

(j) New Requirement: Parts Installation 

After 120 months after the effective date of 

this AD: No person may install a MLG piston, 

P/N 41141–3, or a MLG unit equipped with 

a MLG piston P/N 41141–3, on any airplane. 

(k) New Requirement: Revising the Airplane 

Maintenance Program 

Within two months after the effective date 

of this AD: Revise the airplane maintenance 

program by incorporating Task 321100–01– 

16, inspection of the MLG piston, and 

associated thresholds and intervals described 

in Fokker Engineering Report, MRB 

Appendix 1, SE–623, Issue 8, dated March 

17, 2011. The initial compliance time for 

Task 321100–01–16 is within two months 

after the effective date of this AD. 

(l) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (k) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used other than those specified in Fokker 

Engineering Report, MRB Appendix 1, SE– 

623, Issue 8, dated March 17, 2011, unless 

the actions and intervals are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (m)(1) of this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(n) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0159, dated August 26, 2011; and the service 

information specified in paragraphs (n)(1)(i) 

through (n)(1)(iv) of this AD; for related 

information. 

(i) Fokker Service Bulletin SBF100–32– 

161, dated April 7, 2011. 

(ii) Fokker Services Engineering Report, 

MRB Appendix 1, SE–623, Issue 8, dated 

March 17, 2011. 

(iii) Goodrich Service Bulletin 41000–32– 

29, dated November 10, 2010. 

(iv) Fokker Service Bulletin SBF100–32– 

158, dated October 2, 2009. 

(2) For Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. For 

Goodrich service information identified in 

this AD, contact Goodrich, 1400 South 

Service Road, West Oakville, L6L 5Y7, 

Ontario, Canada, telephone +1–905–827– 

7777; fax +1–905–825–1583; Internet http:// 

www.goodrich.com/TechPubs. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on June 12, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15166 Filed 6–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0642; Directorate 

Identifier 2011–NM–262–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (OPERATIONS) LIMITED 

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 

BAE SYSTEMS (OPERATIONS) 

LIMITED Model BAe 146 series 

airplanes and Model Avro 146–RJ series 

airplanes. This proposed AD was 

prompted by hydraulic pipe ruptures in 

the center of the cabin resulting in 

passengers being contaminated with 

hydraulic fluid. This proposed AD 

would require installing a hydraulic 

fluid containment system. We are 

proposing this AD to prevent harmful or 

hazardous concentrations of hydraulic 

fluid or hydraulic vapor from entering 

the passenger compartment, possibly 

resulting in injury to the passengers. 

DATES: We must receive comments on 

this proposed AD by August 6, 2012. 

ADDRESSES: You may send comments 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, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact BAE 

SYSTEMS (OPERATIONS) LIMITED, 

Customer Information Department, 

Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; telephone +44 1292 675207; 

fax +44 1292 675704; email 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/ 

Businesses/RegionalAircraft/index.htm. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. 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; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS