39050 Federal Register / Vol. 63, No. 139 /Tuesday, July 21, 1998 / Proposed Rules

October 17, 1995), as revised by Service

Bulletin Change Notice 4A, dated October 16,

1996, references Airbus Service Bulletin

A310–57–2049 and Repair Instruction R571–

49305 as additional sources of service

information for accomplishment of Airbus

Modification 7925H1113.

(2) If any crack is found, prior to further

flight, repair in accordance with a method

approved by the Manager, International

Branch, ANM–116, or the DGAC (or its

delegated agent).

(o) For airplanes listed in Airbus Service

Bulletin A310–57–2047, Revision 2, dated

January 22, 1997: Perform a rotating probe

inspection to detect cracks in the fastener

holes on the left-and right-hand sides of the

rear spar internal angle and tee fitting, in

accordance with Airbus Service Bulletin

A310–57–2047, Revision 2, dated January 22,

1997, at the applicable time specified in Note

2 of paragraph 1.A.(2) of the service bulletin,

or within 1,000 flight cycles after the

effective date of this AD, whichever occurs

later; and thereafter at the intervals specified

in Note 2 of paragraph 1.A.(2) of the service

bulletin. Except as provided by paragraph (t)

of this AD, if any discrepancy is found, prior

to further flight, perform follow-on corrective

actions in accordance with the service

bulletin.

(p) For airplanes listed in Airbus Service

Bulletin A310–57–2050, dated April 23,

1990, as revised by Service Bulletin Change

Notices 0.A., dated September 29, 1992, and

0.B., dated January 6, 1995: Perform a visual

or rotating probe inspection to detect cracks

in the drain holes on the lower skin panel in

the center wing box between frames 42 and

46, in accordance with Airbus Service

Bulletin A310–57–2050, dated April 23,

1990, as revised by Service Bulletin Change

Notices 0.A., dated September 29, 1992, and

0.B., dated January 6, 1995, at the applicable

time specified in Note 1 of paragraph 1.A.(2)

of the service bulletin, or within 1,000 flight

cycles after the effective date of this AD,

whichever occurs later; and thereafter at

intervals not to exceed those specified in

Note 1 of paragraph 1.A.(2) of the service

bulletin. Except as provided by paragraph (t)

of this AD, if any discrepancy is found, prior

to further flight, perform follow-on corrective

actions in accordance with the service

bulletin. Accomplishment of Airbus

Modification number 6130S6815 (Airbus

Service Bulletin A310–57–2048), constitutes

terminating action for the repetitive

inspections required by paragraph (p) of this

AD.

(q) For airplanes listed in Airbus Service

Bulletin A310–53–2074, Revision 1, dated

February 20, 1995: Perform visual and eddy

current inspections to detect damaged

sealant, corrosion, and cracks in accordance

with Airbus Service Bulletin A310–53–2074,

Revision 1, dated February 20, 1995.

Accomplish these requirements at the

applicable time specified in Table 2 of

paragraph 1.C.(4) of the service bulletin, or

within 1,000 flight cycles after the effective

date of this AD, whichever occurs later; and

thereafter at intervals not to exceed those

specified in Table 2 of paragraph 1.C.(4) of

the service bulletin, as applicable. Except as

provided by paragraph (t) of this AD, if any

discrepancy is found, prior to further flight,

perform follow-on corrective actions in

accordance with the service bulletin.

(r) For airplanes listed in Airbus Service

Bulletin A310–57–2064, dated August 24,

1995: Perform an eddy current inspection to

detect cracks of the upper corner angle fitting

and the vertical tee fitting at left and right

frame 40, in accordance with Airbus Service

Bulletin A310–57–2064, dated August 24,

1995. Perform the inspection at the time

specified in paragraph (r)(1) or (r)(2) of this

AD, as applicable. Except as provided by

paragraph (t) of this AD, if any crack is

found, prior to further flight, perform

corrective actions in accordance with the

service bulletin.

(1) For Model A310–200 series airplanes:

Prior to the accumulation of 18,000 total

flight cycles, or within 2,000 flight cycles

after the effective date of this AD, whichever

occurs later; and thereafter at intervals not to

exceed 11,000 flight cycles.

(2) For Model A310–300 series airplanes:

Prior to the accumulation of 18,000 total

flight cycles, or within 1,700 flight cycles

after the effective date of this AD, whichever

occurs later; and thereafter at intervals not to

exceed 7,700 flight cycles.

(s) For airplanes listed in Airbus Service

Bulletin A310–57–2038, Revision 2, dated

January 4, 1996: Prior to the accumulation of

12,000 total flight cycles, or within 1,500

flight cycles after the effective date of this

AD, whichever occurs later, perform a high

frequency eddy current (HFEC) or X-ray

inspection to detect cracking of the stringer

runouts inboard and outboard of rib 14 at

stringers 6, 7, 8, and 9, in accordance with

Airbus Service Bulletin A310–57–2038,

Revision 2, dated January 4, 1996. Thereafter,

repeat the inspection at intervals not to

exceed those specified in paragraph 1.B.(5) of

the service bulletin, as applicable. If any

crack is detected, prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, or the DGAC (or its delegated agent).

(t) If any crack is found during any

inspection required by this AD, and the

applicable service bulletin specifies to

contact Airbus for an appropriate action Prior

to further flight, repair in accordance with a

method approved by either the Manager,

International Branch, ANM–116, or the

DGAC (or its delegated agent).

(u) 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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(v) 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 5: The subject of this AD is addressed

in French airworthiness directive 92–106–

132(B)R4, dated June 5, 1996.

Issued in Renton, Washington, on July 14,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–19332 Filed 7–20–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–39–AD]

RIN 2120–AA64

Airworthiness Directives; Mitsubishi

Heavy Industries, Ltd. MU–2B Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Mitsubishi Heavy Industries, Ltd.

(Mitsubishi) MU–2B series airplanes.

The proposed AD would require

inspecting each forward attachment

fitting bolt (total of four bolts) of the

wing tip tanks for the correct bolt and

replacing any incorrect bolt. The

proposed AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for Japan. The actions

specified by the proposed AD are

intended to prevent the wing tip tank

from separating from the airplane

because of an incorrect bolt corroding,

which could result in loss of control of

the airplane.

DATES: Comments must be received on

or before August 25, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–39–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Mitsubishi MU–2 Service Bulletin

(SB) No. 225, dated September 29, 1995,

may be obtained from Mitsubishi Heavy

Industries, Ltd., Nagoya Aerospace

Systems Works, 10, OYE–CHO,

MINATO–KU, Nagoya, Japan,

telephone: NAGOYA (611) 2141,
Federal Register / Vol. 63, No. 139 /Tuesday, July 21, 1998 / Proposed Rules 39051

facsimile: 4464561HISI. Mitsubishi

MU–2 SB No. 089/57–002A, dated

November 5, 1996, may be obtained

from the Raytheon Aircraft Company,

9709 East Central, Wichita, Kansas

67201, Attention: Manager,

Publications. This service information

also may be examined at the Rules

Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

William Roberts, Aerospace Engineer,

Los Angeles Aircraft Certification

Office, FAA, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone: (562) 627–5228; facsimile:

(562) 627–5210.

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, 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 that

summarizes 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 No. 98–CE–39–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, Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–CE–39–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

The Japan Civil Aviation Bureau

(JCAB), which is the airworthiness

authority for Japan, notified the FAA

that an unsafe condition may exist on

certain Mitsubishi MU–2B series

airplanes. The JCAB reports one

instance of corrosion on an incorrect

forward attachment fitting bolt of the

wing tip tank on one of the abovereference airplanes. An incorrect bolt(s)

could be installed on other MU–2B

series airplanes.

Correct bolts, Mitsubishi part number

(P/N) 017A–12887, P/N 017A–12887–3,

and P/N 017A–12887–7, are plated with

a dry lubricant film that is black in color

and is corrosion resistant. The incorrect

bolts, P/N NAS1107, are cadmium

plated, have a gold or yellowish color,

and are not corrosion resistant.

This condition, if not detected and

corrected, could result in the wing tip

tank separating from the airplane with

consequent loss of control of the

airplane.

Relevant Service Information

Mitsubishi Heavy Industries, Ltd., has

issued Mitsubishi MU–2 Service

Bulletin (SB) No. 225, dated September

29, 1995, and Raytheon has issued

Mitsubishi MU–2 SB No. 089/57–002A,

dated November 5, 1996. These service

bulletins specify procedures for

inspecting all forward attachment fitting

bolts of the wing tip tanks to determine

whether any P/N 017A–12887, P/N

017A–12887–3, or 017A–12887–7 bolt is

installed, and replacing any bolt not

incorporating one of these part numbers.

The P/N 017A–12887–7 bolts are of

similar design to the P/N 017A–12887

and P/N 017A–12887–3 bolts and are

identified with the black painted letters

‘‘SPL’’. These service bulletins also

specify procedures for identifying any

P/N 017A–12887 and P/N 017A–12887–

3 bolts with the letters ‘‘SPL’’.

Mitsubishi Heavy Industries, Ltd.,

holds both Type Certificate No. A2PC

and Type Certificate No. A10SW for the

MU–2B series airplanes. Raytheon

manufactures, in the United States, the

airplanes affected by Type Certificate

No. A10SW under a licensing agreement

with Mitsubishi Heavy Industries, Ltd.

The JCAB classified MHI SB 225,

dated September 29, 1995, as mandatory

and issued Japanese AD KU–KI–158

TCD–4310–96, dated March 25, 1996, in

order to assure the continued

airworthiness of the airplanes affected

by Type Certificate No. A2PC that are

certificated for operation in Japan.

The FAA’s Determination

The airplane models listed in Type

Certificate A2PC are manufactured in

Japan and are type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the JCAB has kept the FAA informed of

the situation described above.

The FAA has examined the findings

of the JCAB; reviewed all available

information, including the service

information referenced above; and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States, including the Mitsubishi MU–2B

series airplanes manufactured in the

United States by licensing agreement

and listed in Type Certificate No.

A10SW.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Mitsubishi Models

MU–2B, MU–2B–10, MU–2B–15, MU–

2B–10, MU–2B–25, MU–2B–26, MU–

2B–26A, MU–2B–30, MU–2B–35, MU–

2B–36, MU–2B–36A, MU–2B–40, and

MU–2B–60 airplanes of the same type

design registered in the United States,

the FAA is proposing AD action. The

proposed AD would require inspecting

each forward attachment fitting bolt

(total of four bolts) of the wing tip tanks

to determine whether any bolt

incorporating P/N 017A–12887, P/N

017A–12887–3, or 017A–12887–7 is

installed, and replacing any bolt not

incorporating one of these part numbers,

with a P/N 017A–12887–7 bolt. The P/

N 017A–12887–7 bolts are of similar

design to the P/N 017A–12887 and P/N

017A–12887–3 bolts, and are identified

with the black painted letters ‘‘SPL’’.

The proposed AD would also require

identifying any P/N 017A–12887 or P/

N 017A–12887–3 bolt with the letters

‘‘SPL’’. Accomplishment of the

proposed installation would be in

accordance with the service information

previously referenced.

Cost Impact

The FAA estimates that 252 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 1 workhour per airplane

to accomplish the proposed inspection,

and that the average labor rate is

approximately $60 an hour. Based on

these figures, the total cost impact of the

proposed inspection on U.S. operators is

estimated to be $15,120, or $60 per

airplane.

Any replacements that would be

required by the proposed AD would

take approximately 4 workhours per

airplane with each bolt costing $350 (up

to 4 bolts per airplane). If an airplane

had four incorrect bolts installed, the
39052 Federal Register / Vol. 63, No. 139 /Tuesday, July 21, 1998 / Proposed Rules

replacement cost of the proposed AD

would be $1,640 for that airplane.

Regulatory Impact

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 action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); 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 has been placed 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

(AD) to read as follows:

Mitsubishi Heavy Industries, Ltd.: Docket

No. 98–CE–39–AD.

Applicability: The following airplane

model and serial number airplanes:

Models Serial Nos.

Type Certificate No. A2PC

MU–2B, MU–2B–10,

MU–2B–15, MU–

2B–20, MU–2B–25,

and MU–2B–26.

008 through 347.

MU–2B–30, MU–2B–

35, and MU–2B–36.

501 through 651, 653

through 660, and

662 through 696.

Type Certificate No. A10SW

MU–2B–25, MU–2B–

26, MU–2B–26A,

and MU–2B–40.

313SA, 321SA, and

348SA through

459SA.

MU–2B–35, MU–2B–

36A, and MU–2B–

60.

652SA, 661SA, and

697SA through

1569SA.

Note 1: Mitsubishi Heavy Industries, Ltd.

holds both Type Certificate No. A2PC and

Type Certificate No. A10SW for the affected

airplanes. Raytheon manufactures, in the

United States, the airplanes affected by Type

Certificate No. A10SW under a licensing

agreement with Mitsubishi Heavy Industries,

Ltd.

Note 2: 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 request approval for an

alternative method of compliance in

accordance with paragraph (e) 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 as indicated in the

body of this AD, unless already

accomplished.

To prevent the wing tip tank from

separating from the airplane because of an

incorrect bolt corroding, which could result

in loss of control of the airplane, accomplish

the following:

(a) Within the next 100 hours time-inservice (TIS) after the effective date of this

AD, inspect each forward attachment fitting

bolt (total of four bolts) of the wing tip tanks

to determine whether any bolt not

incorporating part number (P/N) 017A–

12887, P/N 017A–12887–3, or 017A–12887–

7, is installed. Accomplish this inspection in

accordance with whichever of the following

is applicable:

(1) Mitsubishi MU–2 Service Bulletin No.

225, dated September 29, 1995, for airplanes

affected by Type Certificate No. A2PC; or

(2) Mitsubishi MU–2 Service Bulletin No.

089/57–002A, dated November 5, 1996, for

airplanes affected by Type Certificate No.

A10SW.

(b) If any bolt not incorporating P/N 017A–

12887, P/N 017A–12887–3, or 017A–12887–

7, is installed, prior to further flight, replace

it with a P/N 017A–12887–7 bolt. The P/N

017A–12887–7 bolts are of similar design to

the P/N 017A–12887 and P/N 017A–12887–

3 bolts, and are identified with the black

painted letters ‘‘SPL’’. Accomplish this

action in accordance with one of the service

bulletins listed in paragraphs (a)(1) and (a)(2)

of this AD, as applicable.

(c) If any P/N 017A–12887 or P/N 017A–

12887–3 bolt is installed, prior to further

flight, identify the bolt with the letters

‘‘SPL’’. Accomplish this action in accordance

with one of the service bulletins listed in

paragraphs (a)(1) and (a)(2) of this AD, as

applicable.

(d) 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.

(e) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Los Angeles

Aircraft Certification Office (ACO), FAA,

3960 Paramount Blvd., Lakewood, California

90712. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(f) Questions or technical information

related to Mitsubishi MU–2 Service Bulletin

No. 225, dated September 29, 1995, should

be directed to Mitsubishi Heavy Industries,

Ltd., Nagoya Aerospace Systems Works, 10,

OYE–CHO, MINATO–KU, Nagoya, Japan,

telephone: NAGOYA (611) 2141, facsimile:

4464561HISI. Questions or technical

information related to Mitsubishi MU–2

Service Bulletin No. 089/57–002A, dated

November 5, 1996, should be directed to

Raytheon Aircraft Company, 9709 East

Central, Wichita, Kansas 67201, Attention:

Manager, Publications. This service

information may be examined at the FAA,

Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

Note 4: The subject of this AD is addressed

in Japanese AD KU–KI–158 TCD–4310–96,

dated March 25, 1996.

Issued in Kansas City, Missouri, on July 14,

1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–19330 Filed 7–20–98; 8:45 am]

BILLING CODE 4910–13–P