Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules 10241

that the information contained in the general

revisions is identical to that specified in the

TR documents.

Structural Inspections

(2) For airplanes having closing angles that

are identified as principal structural

elements: Do the inspections specified by the

applicable TR listed in Table 1 of paragraph

(a) of this AD. Thereafter, repeat the

inspection at intervals not to exceed 10,000

flight cycles at the time specified in

paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii) of

this AD, as applicable.

(i) For airplanes that have accumulated less

than 8,000 flight cycles as of the effective

date of this AD: Do the threshold inspection

prior to the accomplishment of 10,000 flight

cycles, or within 2,000 flight cycles after the

effective date of this AD, whichever occurs

later.

(ii) For airplanes that have accumulated

8,000 flight cycles or more as of the effective

date of this AD: Do the threshold inspection

within 2,000 flight cycles after the effective

date of this AD.

(iii) For airplanes on which a 40,000 flight

cycle inspection specified by the applicable

TR listed in Table 1 of paragraph (a) of this

AD has been done, no cracks have been

found, and/or the closing angles have been

replaced: Start the 10,000 flight cycle

repetitive inspection at the time specified by

either paragraph (a)(2)(iii)(A) or (a)(2)(iii)(B)

of this AD, as applicable.

(A) From the date at which the 40,000

flight cycle inspection was done.

(B) From the date the closing angles were

replaced.

Corrective Actions

(b) If any crack is detected during any

structural inspection required by paragraph

(a)(2) of this AD, before further flight, repair

any such cracking or replace the closing

angles per a method approved by the

Manager, New York Aircraft Certification

Office (ACO), FAA, or the Transport Canada

Civil Aviation (or its delegated agent). For a

repair or replacement method to be approved

by the Manager, New York ACO, as required

by this paragraph, the Manager’s approval

letter must specifically reference this AD.

(c) Except as provided by paragraph (d) of

this AD: After the actions specified in

paragraphs (a) and (b) of this AD have been

accomplished, no alternative inspections or

inspection intervals may be approved for the

structural elements specified by the

documents listed in Table 1 of paragraph

(a)(1) of this AD.

Alternative Methods of Compliance

(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, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with sections 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.

Note 4: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–07, dated March 3, 2000.

Issued in Renton, Washington, on February

7, 2001.

Dorenda D. Baker,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–3674 Filed 2–13–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–38–AD]

RIN 2120–AA64

Airworthiness Directives; Marathon

Power Technologies Company

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes

adopting a new airworthiness directive

(AD) for certain nickel cadmium

batteries produced by Marathon Power

Technologies Company (Marathon). The

AD would require visually inspecting

screws installed on Marathon batteries

and replacing certain unairworthy

screws. This proposal is prompted by an

explosion of a G.E./Saft battery due to

failure of an unairworthy screw. Certain

Marathon batteries are a similar design

and could have the same unairworthy

screws. The actions specified by the

proposed AD are intended to prevent an

explosion of a battery, structural

damage, and subsequent loss of power

to the electrical systems.

DATES: Comments must be received on

or before April 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

38–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

address: 9–asw–adcomments@faa.gov.

Comments may be inspected at the

Office of the Regional Counsel between

9 a.m. and 3 p.m., Monday through

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT:

Aaron Cornelius, Aviation Safety

Engineer, FAA, Special Certification

Office, Fort Worth, TX 76193–0190;

telephone (817) 222–4637, fax (817)

222–5785.

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

should 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 will be

considered before taking action on the

proposed rule. The proposals contained

in this document 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 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 mailed

comments submitted in response to this

proposal must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2000–SW–

38–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, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 2000–SW–38–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

This document proposes adopting a

new AD for certain nickel cadmium

batteries produced by Marathon. The

AD would require inspecting any

affected battery to verify that each #10–

32 socket head cap screw (screw) is part

number (P/N) 10488–020 with two rows

of straight knurls, which is the correct

screw hardware. This AD also requires,

before further flight, replacing any

screw found with only one knurl or no

knurl with a screw, P/N 10488–020,

with two knurls. This proposal is

10242 Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules

prompted by an explosion of a G.E./Saft

battery during routine maintenance on a

McDonnell Douglas DC–9 aircraft.

Marathon battery, P/N 27183–001, is

similar to the GE/Saft battery that

exploded. A battery cell screw head

broke off causing an electrical short

circuit between the internal battery cell

positive and negative posts. This

resulted in a rapid discharge of energy,

heat, and gases. Investigation revealed

unapproved screws were installed, and

maintenance procedures did not comply

with the manufacturer’s

recommendations. Metallurgical tests

cited chloride as a factor in causing the

heads of the failed screws to shear and

the eventual explosion of the battery.

The actions specified by the proposed

AD are intended to prevent an explosion

of a battery, structural damage, and

subsequent loss of power to the

electrical systems.

We have identified an unsafe

condition that is likely to exist or

develop on other aircraft with Marathon

batteries installed that are similar in

design to the GE/Saft battery that

exploded. Both are designed with

similar #10–32 screws, P/N 10488–020.

The proposed AD would require

visually inspecting each #10–32 screw

in certain Marathon batteries within 12

months or the next scheduled battery

maintenance and, before further flight,

replacing any unairworthy screw with

an airworthy screw, P/N 10488–020.

The FAA estimates that 1814 aircraft

would be affected by this proposed AD,

that it would take approximately 2 work

hours to replace any unairworthy

screws with airworthy screws for each

battery, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $100 per

battery if all screws were replaced.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $399,080.

The regulations proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

Marathon Power Technologies Company:

Docket No. 2000–SW–33–AD.

Applicability: Marathon Power

Technologies Company (Marathon) nickel

cadmium batteries, installed in but not

limited to the aircraft models shown in Table

1, certificated in any category:

TABLE 1

Marathon P/N Battery type Airframe manufacturer Model aircraft

31718–002 ... TCA–1742 Aerospatiale ................................................................... ATR 42, 72 Series

27515–002 ... CTCA–21H–1 Agusta ............................................................................ 119 Koala

30703–002 ... TMA–5–20C Agusta ............................................................................ 412/212

29365–01C ... CA–1700 Bell Helicopter Textron, Inc. (BHTI) ............................... 206A, B, L

30450–001 ... CA–170A BHTI ............................................................................... 206L–1, L–3

30135–001 ... SP–1700 BHTI ............................................................................... 206A, B, L

30135–002 ... SP–1700L BHTI ............................................................................... 206A, B, L

30554–01C ... SP–170A BHTI ............................................................................... 206L–1, L–3

32007–001 ... SP–170AL BHTI ............................................................................... 206l–1, 206l–2

32703–001 ... TMA–5–20 BHTI ............................................................................... 204B, 205A, 205A–1, 212, 222, 222B, 222U, 412

31871–001 ... TSP–1722 BHTI ............................................................................... 222, 222B

26069–001 ... KCA–727 Boeing ............................................................................ 727 Series

29986–001 ... TCA–7 Boeing ............................................................................ 234

31918–001 ... TSP–1760L Bombardier/Canadair ..................................................... CL 600–2B19

29094–002 ... BTCA–5–20 British Aerospace (Jetstream) ....................................... 3101, 3201

31392–002 ... TSP–940 British Aerospace (Raytheon Corporate Jets Ltd) ......... 146 Series 100A, 200A

30250–001 ... BTCA–9–20A British Aerospace (Jetstream) ....................................... 3101, 3201

29486–001 ... ATCA–21H Cessna ........................................................................... 441

29094–001 ... BTCA–5 DeHavilland (Boeing Canada) ....................................... DHC–6–1, –100, 200, 300, DHC–7–1, –100, –101,

–102, –103

29360–002 ... BTMA–5–20 Embraer ......................................................................... EMB 110P1, 110P2

29206–001 ... CA–91–20 Fairchild (Swearingen) ................................................... SA26AT, SA226T, SA226AT, SA226T(B), SA226TC

28974–001 ... CA–9–20 Fairchild (Swearingen) ................................................... SA26AT, SA226T, SA226AT, SA226T(B), SA226TC

29341–001 ... CA–20H–20 Fokker ............................................................................ F27 Series

29017–002 ... TCA–5–20–1 Learjet ............................................................................ 24, 25, 35

30839–001 ... CA–139 McDonnell Douglas ........................................................ DC–9 Series

30695–001 ... TCA–1753 McDonnell Douglas (Hughes) ........................................ 369D, H, HM, HE, serial number (S/N) 001 thru 1308,

369HS S/N 781S thru 874S

30896–001 ... TCA–1754 McDonnell Douglas (Hughes) ........................................ 369HS S/N 001S thru 780S

30695–002 ... TCA–1753 McDonnell Douglas (Hughes) ........................................ 369D, H, HM, HE, S/N 001 thru 1308, 369HS S/N

781S thru 874S

Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules 10243

TABLE 1—Continued

Marathon P/N Battery type Airframe manufacturer Model aircraft

30900–001 ... TSP–1754 McDonnell Douglas (Hughes) ........................................ 369HS S/N 001S thru 780S

30949–001 ... TSP–1755 McDonnell Douglas (Hughes) ........................................ 369D S/N 1309 & Sub., E S/N 125 & Sub., F S/N 55 &

sub., FF S/N 55 & Sub.

30703–001 ... TMA–5–20 Piaggio ........................................................................... P–166DL3, P–166

29248–001 ... KTCA–21H–

20

Short Brothers ................................................................ SD3–30

29487–002 ... CA–176 Sikorsky ......................................................................... S76A Series

29490–001 ... CA–376 Sikorsky ......................................................................... S76A Series

31202–001 ... SP–276 Sikorsky ......................................................................... S76B Series

27183–001 ... CA–13 McDonnell Douglas ........................................................ DC–9, MD–80

Note 1: This AD applies to each aircraft

identified in the preceding applicability

provision that incorporates one or more of

the affected batteries, regardless of whether it

has been otherwise modified, altered, or

repaired in the area subject to the

requirements of this AD. For aircraft that

have been modified, altered, or repaired so

that the performance of the requirements of

this AD is affected, the owner/operator must

request approval for an alternative method of

compliance in accordance with paragraph (b)

of this AD. The request should include an

assessment of the effect of the modification,

alteration, or repair on the unsafe condition

addressed by this AD; and if the unsafe

condition has not been eliminated, the

request should include specific proposed

actions to address it.

Compliance: Required within 12 months or

the next scheduled battery maintenance,

whichever occurs first.

To prevent an explosion of the battery,

structural damage, and subsequent loss of

power to the electrical systems, accomplish

the following:

(a) Visually inspect each #10–32 screw in

the battery at the terminals to verify that each

screw has two (2) rows of straight knurls (see

Figure 1). If a screw is found with only one

knurl or no knurl (see Figure 1), before

further flight, fully discharge the battery,

remove the unairworthy screw and replace it

with an airworthy screw, P/N 10488–020.

(b) 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, Special

Certification Office, Rotorcraft Directorate,

FAA. Operators shall submit their requests

through an FAA Principal Maintenance

Inspector, who may concur or comment and

then send it to the Manager, Special

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Special Certification

Office.

(c) Special flight permits may be issued in

accordance with sections 14 CFR 21.197 and

21.199 to operate the aircraft to a location

where the requirements of this AD can be

accomplished.

Issued in Fort Worth, Texas, on February

2, 2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–3673 Filed 2–13–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–298–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9, DC–9–80, and C–

9 (Military) Series Airplanes; Model

MD–88 Airplanes; and Model MD–90

Airplanes

AGENCY: Federal Aviation

Administration, DOT.