Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules 19181

MPG reference No. Reason

52–10–6R .... Required by AD 87–21–06,

amendment 39–5744.

53–10–29R .. Will be addressed in a separate rulemaking action.

(c) Within one year after November 3, 1988

(the effective date of AD 87–24–06 R1,

amendment 39–6037), or prior to the

accumulation of the number of landings

listed in the landing threshold indicated in

British Aerospace BAC 1–11 Alert Service

Bulletin 51–A–PM5830, Issue 3, dated March

19, 1987, whichever occurs later, and

thereafter, at intervals not to exceed the

number of landings specified in the alert

service bulletin, accomplish the inspections,

repairs, and replacements, as necessary, of

the Structural Significant Items identified in

Tables 1, 2, and 3 of that service bulletin.

(d) Within one year after the effective date

of this AD, or prior to the accumulation of

the number of landings listed in the landing

threshold indicated in British Aerospace

BAC 1–11 Alert Service Bulletin 51–A–

PM5830, Issue 4, dated January 28, 1993,

whichever occurs later, and thereafter, at

intervals not to exceed the number of

landings specified in the alert service

bulletin, accomplish the inspections, repairs,

and replacements, as necessary, of the

Structural Significant Items identified in

Tables 1 (except Maintenance Planning

Guide Reference Numbers 52–10–6R and 53–

10–29R), 2, and 3 of the alert service bulletin.

Note 3: For operators that have

accomplished this inspection previously in

accordance with the requirements of AD 87–

24–06 R1, amendment 39–6037: This

paragraph requires that the next scheduled

inspection for that SSI be performed within

the repetitive interval specified for that SSI

in the alert service bulletin after the last

inspection performed in accordance with the

requirements of AD 87–24–06 R1 for that SSI.

(e) For any cracked structure detected

during any inspection required by this AD,

prior to further flight, accomplish paragraph

(e)(1), (e)(2), or (e)(3) of this AD.

(1) Replace the cracked part with a

serviceable part of the same part number, in

accordance with the Airplane Maintenance

Manual. Or

(2) Repair the cracked structure in

accordance with the Structural Repair

Manual, listed in the service bulletin. Or

(3) Repair in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate.

(f) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on April 11,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–9347 Filed 4–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–40–AD]

Airworthiness Directives; Boeing

Model 737 Series Airplanes Equipped

With BFGoodrich Main Landing Gear

Brake Assemblies

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Boeing Model 737 series

airplanes. This proposal would require

inspection of certain brake assemblies to

determine the part number of the torque

plates, measurement of the amount of

wear remaining on the brake wear pin

indicator, and removal of brake

assemblies on which misidentified

torque plates were installed and

replacement with serviceable brakes.

This proposal is prompted by a report

that certain torque plates were

misidentified and installed on certain

brake assemblies. The actions specified

by the proposed AD are intended to

prevent decreased brake performance

during a rejected takeoff or landing

when these brakes are at or near their

indicated wear limit. (The brake wear

pin indicator would falsely indicate

longer remaining wear because of the

misidentified longer torque plates that

were installed on these brake

assemblies.)

DATES: Comments must be received by

May 11, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

40–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

BFGoodrich Aerospace, Aircraft Wheels

and Brakes, P.O. Box 340, Troy, Ohio

45373. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

David M. Herron, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2672; fax (206) 227–1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–40–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

94–NM–40–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Recently, BFGoodrich shipped some

torque plates that were misidentified as
19182 Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules

part number (P/N) 184–875, when, in

reality, they were P/N 184–884. These

misidentified torque plates were

installed on Boeing Model 737 series

airplanes with main landing gear brake

assemblies having BFGoodrich P/N’s 2–

1474–1, –2, –3, and –5 (Boeing P/N’s

10–61819–22, –26, –27, and –31).

Torque plates having P/N 184–884

should be installed on brake assemblies

having P/N 2–1474–7. Although these

two torque plates are similar in

appearance, the essential difference is

that torque plates having P/N 184–884

are 0.240 inch longer than torque plates

having P/N 184–875. Therefore, the

FAA has determined that brake

assemblies having BFGoodrich P/N 2–

1474–1, –2, –3, or –5 on which the

misidentified torque plates were

installed, would falsely indicate a

longer remaining wear on the brake

wear pin indicator. This condition, if

not corrected, could result in decreased

brake performance during a rejected

takeoff or landing when these brakes are

at or near their indicated wear limit.

BFGoodrich has issued Service

Bulletin 2–1474–32–17, dated January

26, 1995, which describes procedures

for a one-time inspection of the brake

assemblies on Model 737 series

airplanes to determine the P/N of the

torque plates. This service bulletin also

describes procedures for measurement

of the amount of wear remaining on the

brake wear pin indicator, and removal

of brake assemblies having BFGoodrich

P/N 2–1474–1, –2, –3, or –5 on which

the misidentified torque plates were

installed and replacement with

serviceable brakes.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require a one-time inspection of certain

brake assemblies on Model 737 series

airplanes to determine the P/N of the

torque plates. This proposed AD would

also require measurement of the amount

of wear remaining on the brake wear pin

indicator, and removal of brake

assemblies on which misidentified

torque plates were installed and

replacement with serviceable brakes.

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

This proposal permits, for a period of

up to 30 days after the effective date of

the rule, installation of brake assemblies

having BFGoodrich P/N 2–1474–1, –2,

–3, or –5 on which misidentified torque

plates, P/N 184–884, have been

installed. The FAA has determined such

replacement will not compromise safety

of the fleet since the life expectancy of

these brakes is typically 90 to 120 days.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been included in this notice to clarify

this long-standing requirement.

There are approximately 717 Model

737 series airplanes equipped with

BFGoodrich main landing gear brake

assemblies of the affected design in the

worldwide fleet. The FAA estimates that

325 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 0.25 work

hour per airplane to accomplish the

proposed actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $4,875, or $15 per

airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

The regulations proposed herein

would not have substantial direct effects

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. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that 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); and (3) if

promulgated, 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. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 95–NM–40–AD.

Applicability: Model 737 series airplanes

equipped with BFGoodrich main landing

gear brake assemblies having part numbers

(P/N) 2–1474–1, –2, –3, or –5 (Boeing P/N’s

10–61819–22, –26, –27, or –31); certificated

in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent decreased brake performance

during a rejected takeoff or landing when

these brakes are at or near their indicated

wear limit, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform an inspection of the

brake assembly to determine the part number

(P/N) of the torque plate, in accordance with

BFGoodrich Service Bulletin 2–1474–32–17,

dated January 26, 1995.
Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules 19183

(b) If the P/N is 184–790, –790–1, –790–2,

–790–3, or –875, no further action is required

by this paragraph.

(c) If the P/N does not coincide with one

identified in paragraph (b) of this AD, prior

to further flight, measure the amount of wear

remaining on the brake wear pin indicator, in

accordance with service bulletin. Remove

and replace the brake prior to the time

specified in paragraph (c)(1), (c)(2), or (c)(3)

of this AD, as applicable.

(1) If the remaining wear on the brake wear

pin indicator is equivalent to 0.260 inch or

more: Prior to the accumulation of 40 flight

cycles, remove that brake assembly and

replace it with a serviceable brake assembly,

in accordance with the service bulletin. If the

brake assembly is replaced with a brake

assembly having BFGoodrich P/N 2–1474–1,

–2, –3, or –5 on which a torque plate having

P/N 184–884 has been installed, replace that

brake assembly prior to the accumulation of

40 flight cycles since installation. As of 30

days after the effective date of this AD, no

person shall install on any airplane, a brake

assembly, BFGoodrich P/N 2–1474–1, –2, –3,

or –5 (Boeing P/N 10–61819–22, –26, –27, or

–31), on which a torque plate having P/N

184–884 has been installed.

(2) If the remaining wear on the brake wear

pin indicator is less than 0.260 inch but more

than 0.240 inch: Remove that brake assembly

and replace it with a serviceable brake

assembly, in accordance with the service

bulletin. Use the following formula to

determine when the brake assembly must be

removed and replaced: (measurement of wear

remaining on brake wear pin indicator) ¥

(0.240 inch) × (1,000 flight cycles) = (time,

expressed in number of flight cycles, prior to

which brake assembly must be removed and

replaced). As of 30 days after the effective

date of this AD, no person shall install on

any airplane, a brake assembly, BFGoodrich

P/N 2–1474–1, –2, –3, or –5 (Boeing P/N 10–

61819–22, –26, –27, or –31), on which a

torque plate having P/N 184–884 has been

installed.

(3) If the remaining wear on the brake wear

pin indicator is equivalent to 0.240 inch or

less: Prior to further flight, remove that brake

assembly and replace it with a serviceable

brake assembly, in accordance with the

service bulletin. As of 30 days after the

effective date of this AD, no person shall

install on any airplane, a brake assembly,

BFGoodrich P/N 2–1474–1, –2, –3, or –5

(Boeing P/N 10–61819–22, –26, –27, or –31),

on which a torque plate having P/N 184–884

has been installed.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(e) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on April 11,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–9348 Filed 4–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–NM–105–AD]

Airworthiness Directives; Raytheon

Corporate Jets Model BAe 125–800A

and –1000A Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Raytheon

Corporate Jets Model BAe 125–800A

and –1000A airplanes, that would have

required inspections of the wing leading

edge skins, including the wing anti-ice

fluid distribution panel (TKS panel)

rebate and radius; repair, if necessary;

and subsequent corrosion protection

treatment. That proposal was prompted

by reports of corrosion of the wing

leading edge skin at the interface with

the TKS panels. This action revises the

proposed rule by adding inspections

and treatments of the landing/taxiing

lamp window recess and the stall vane

spoiler rebate/radius. The actions

specified by this proposed AD are

intended to prevent reduced structural

integrity of the wing leading edge

section at the interface with the TKS

panels and stall vane spoilers, which

could adversely affect the flight

characteristics of the airplane.

DATES: Comments must be received by

May 26, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 93–NM–

105–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Raytheon Corporate Jets, Inc., 3 Bishops

Square Street, Albans Road West,

Hatfield, Hertfordshire, AL109NE,

United Kingdom. This information may

be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 93–NM–105–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

93–NM–105–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Raytheon Corporate Jets Model BAe

125–800A and –1000A airplanes, was

published as a notice of proposed

rulemaking (NPRM) in the Federal

Register on August 25, 1993 (58 FR